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  • 1
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    Twee nieuwe tweestaarten in Nederland (Diplura) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.43 (2014) p.5
    Details
    Publication Date: 2017-03-16
    Description: Tweestaarten Diplura behoren met de springstaarten Collembola en beentasters Protura tot de Entognatha. Dat zijn kleine ongevleugelde bodemdieren met zes poten, die zich onderscheiden van de insecten door hun verzonken monddelen. Tot nu toe waren twee soorten voor Nederland gemeld, maar voor België 13. Tijdens een onderzoek naar in mierennesten levende organismen werden twee soorten gevonden die nog niet uit Nederland bekend waren. Verder onderzoek zal zeker nog meer nieuwe tweestaarten kunnen opleveren.
    Keywords: Diplura ; Nederland ; Campodea lubbocki ; Campodea plusiochaeta ; verspreiding ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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  • 2
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    De kriebelmuggen van Nederland en Vlaanderen (Diptera: Simuliidae) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.43 (2014) p.67
    Details
    Publication Date: 2017-03-16
    Description: Larven van kriebelmuggen komen uitsluitend voor in stromend water, waar ze met hun waaiervormige monddelen deeltjes filteren uit het voorbij stromende water. Het zijn goede indicatoren voor zuurstofrijk water. Tot nu toe was niet duidelijk welke soorten precies voorkomen in Nederland en België en de determinatie van kriebelmuggen wordt vaak als lastig beschouwd. Om dit te verhelpen, presenteren we hier determinatietabellen voor alle in Nederland en België voorkomende soorten, zowel voor larven van het laatste stadium als voor poppen.
    Keywords: Diptera ; Simuliidae ; Nederland ; België ; herkenning ; verspreiding ; ecologie ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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  • 3
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    Recente aanvullingen op de Nederlandse loopkevercatalogus (Coleoptera: Carabidae) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.43 (2014) p.17
    Details
    Publication Date: 2017-03-16
    Description: De catalogus van de Nederlandse kevers uit 2010 geeft het meest recente overzicht van de Nederlandse kevers. Er staan 372 soorten loopkevers op deze lijst. Per soort wordt een overzicht gegeven van de provincies waaruit waarnemingen bekend zijn. Voor elk zogenaamd provincierecord is een collectie-exemplaar aangeduid als bewijsexemplaar. Sinds 2010 is er veel nieuwe informatie over loopkevers bekend geworden. In dit artikel worden de wijzigingen in de lijst toegelicht.
    Keywords: Coleoptera ; Carabidae ; Nederland ; verspreiding ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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  • 4
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    De reuzenertswesp Leucospis dorsigera nieuw voor Nederland (Hymenoptera: Chalcidoidea) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.43 (2014) p.1
    Details
    Publication Date: 2017-03-16
    Description: Hoe een leek op het gebied van wespen en bijen toch een leuke vondst kan doen. Op zonnige dagen gaat de auteur regelmatig op ‘tuinsafari’. Een tuin waarin rekening wordt gehouden met vogels en insecten, door keuze van beplanting en het ophangen van insectenhotels. De inspanningen leverden op 23 juli 2014 een opvallende wesp op. In een bijna automatische reactie werden snel foto’s gemaakt, in de hoop ze later te kunnen determineren. De wesp vloog daarna weg en werd niet meer gezien. Na determinatie blijkt het reuzenertswesp Leucospis dorsigera te zijn, een nieuwe soort bronswesp voor Nederland.
    Keywords: Hymenoptera ; Chalcidoidea ; Leucospis dorsigera ; Nederland ; herkenning ; biologie ; verspreiding ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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  • 5
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    Twee nieuwe citroenzweefvliegen voor Nederland: Xanthogramma dives en X. stackelbergi (Diptera: Syrphidae) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.43 (2014) p.27
    Details
    Publication Date: 2017-03-16
    Description: De gewone citroenzweefvlieg Xanthogramma pedissequum is een eenvoudig te herkennen zweefvlieg. Tenminste, dat dachten we tot voor kort. Nu blijkt dat de bijna identieke X. dives en X. stackelbergi ook in Nederland rondvliegen. Gelukkig zijn er enkele kenmerken waarmee deze drie soorten citroenzweefvlieg in het veld redelijk herkenbaar blijken. In dit artikel bespreken we deze kenmerken en geven we informatie over verspreiding en vliegtijden van de drie soorten.
    Keywords: Diptera ; Syrphidae ; Xanthogramma dives ; Xanthogramma stackelbergi ; Nederland ; herkenning ; verspreiding ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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  • 6
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    Blaaskopvliegen van het genus Leopoldius in de Benelux (Diptera: Conopidae) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.43 (2014) p.55
    Details
    Publication Date: 2017-03-16
    Description: Wespblaaskoppen Leopoldius worden ondanks hun opvallende uiterlijk maar weinig waargenomen. De soorten zijn lastig van elkaar te onderscheiden en bovendien werden tot voor kort variabele kenmerken gebruikt, wat tot veel verwarring heeft geleid. Nu blijkt dat alleen vrouwtjes met zekerheid te herkennen zijn aan de vorm van het klampje. Dit is een lepelvormig uitsteeksel onder het vijfde achterlijfsegment. Het wordt gebruikt bij het afzetten van eieren op een gastheer. Waarschijnlijk zijn limonadewespen de belangrijkste gastheer van Leopoldius. In dit artikel wordt een nieuwe soort voor België en een nieuwe soort voor Luxemburg gemeld. Daarnaast wordt een overzicht geboden van waarnemingen in Nederland, België en Luxemburg en een sleutel tot de Noordwest-Europese soorten.
    Keywords: Diptera ; Conopidae ; Leopoldius ; Nederland ; België ; Luxemburg ; herkenning ; biologie ; verspreiding ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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  • 7
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    Eerste larvenvondst van de kokerjuffer Molanna albicans buiten Drenthe (Trichoptera: Molannidae) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.43 (2014) p.93
    Details
    Publication Date: 2017-03-16
    Description: Ondanks de fors toegenomen aandacht voor watermacrofauna sinds begin jaren 1980 is de schietmot Molanna albicans maar sporadisch aangetroffen. In dit artikel wordt de eerste larvenvondst van M. albicans buiten Drenthe beschreven. Samen met de vindplaatsen in Drenthe is de soort nu van vijf vennen in Nederland bekend. Aanvullend worden de determinatiekenmerken aan de hand van foto’s geïllustreerd.
    Keywords: Trichoptera ; Molannidae ; Molanna albicans ; Nederland ; verspreiding ; biologie ; herkenning ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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  • 8
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    Spatial and temporal distribution of caddisfly larvae in two lowland streams in The Netherlands (Trichoptera) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.42 (2014) p.81
    Details
    Publication Date: 2017-03-16
    Description: Caddisflies are a species rich insect order. The adults are moth-like, but their wings bear hairs instead of scales. The larvae are aquatic and live in self-constructed cases, made of plant material, sand or debris. The species are used as indicators of water quality, but much is still not known about their biology and ecology. In this paper the preferred substrates and phenology of the larvae of 13 species are described, using the data of a survey of two lowland streams in the east of the Netherlands.
    Keywords: Trichoptera ; ecology ; phenology ; Netherlands ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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  • 9
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    Slakkendodende vliegen van het genus Psacadina in Nederland en België (Diptera: Sciomyzidae) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.42 (2014) p.37
    Details
    Publication Date: 2017-03-16
    Description: Slakkendodende vliegen danken hun naam aan hun roofzuchtige, parasitaire larven, die het op slakken gemunt hebben. Uit België en Nederland zijn circa 60 soorten uit deze familie bekend, maar er zijn er zeker meer te ontdekken. Dit artikel meldt een nieuwe soort voor de Nederlandse fauna uit het genus Psacadina, dat in beide landen drie soorten telt. De herkenning en het voorkomen van de drie soorten wordt uitgebreid besproken.
    Keywords: Diptera ; Sciomyzidae ; Psacadina ; Nederland ; België ; biologie ; herkenning ; verspreiding ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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  • 10
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    De zwarte vlieg Bibio venosus nieuw voor de Nederlandse fauna (Diptera: Bibionidae) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.42 (2014) p.33
    Details
    Publication Date: 2017-03-16
    Description: Zwarte vliegen behoren tot de muggen, maar door hun korte antennen doen ze oppervlakkig aan vliegen denken. De mannetjes zien er met hun grote kop en grote ogen heel anders uit dan de vrouwtjes, die een kleine kop met kleine ogen hebben. In het voorjaar vormen sommige soorten opvallend grote zwermen op windluwe plekken. Aan de 17 soorten die reeds uit Nederland bekend waren, kan er nu één worden toegevoegd: Bibio venosus.
    Keywords: Diptera ; Bibionidae ; Bibio venosus ; herkenning ; biologie ; verspreiding ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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  • 11
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    Uitbreiding van de hooiwagen Astrobunus leavipes (Opiliones) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.42 (2014) p.11
    Details
    Publication Date: 2017-03-16
    Description: Astrobunus laevipes is een hooiwagen die via het Rijnbekken recentelijk ons land is binnengekomen. Er waren al vondsten langs de Waal en Nederrijn in Gelderland en het meest oostelijke puntje van de provincie Utrecht. Door gerichte inventarisaties kunnen wij de hooiwagen nu nieuw voor de provincies Zuid-Holland en Noord-Brabant melden. Daarnaast is er van A. laevipes nu ook een waarneming langs de IJssel en enkele westelijker in de provincie Utrecht. Allerlei rivierbegeleidende biotopen langs (uitlopers van) de Nederrijn en Waal worden al door deze opmerkelijke hooiwagen bevolkt, maar de noordelijke uitbreiding via de IJsselvallei lijkt veel trager te verlopen. De Maas lijkt nog niet bereikt.
    Keywords: Opiliones ; Astrobunus leavipes ; Nederland ; verspreiding ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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  • 12
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    Vierde aanvulling op de naamlijst van Nederlandse sluipvliegen (Diptera: Tachinidae) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.43 (2014) p.43
    Details
    Publication Date: 2017-03-16
    Description: De familie der sluipvliegen is één der soortenrijkste vliegenfamilies in ons land. De larven ontwikkelen zich inwendig in ongewervelden, veelal vlinderrupsen. De familie is in ons land relatief goed bestudeerd. In dit artikel wordt wederom een soort voor het eerst uit ons land vermeld. Hiermee komt het totaal aantal soorten dat in Nederland ooit vastgesteld is op 334.
    Keywords: Diptera ; Tachinidae ; Pexopsis aprica ; Nederland ; verspreiding ; biologie ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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  • 13
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    Bamboewormen in Nederland, met Micromaldane ornithochaeta nieuw voor Nederland (Polychaeta: Maldanidae) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.43 (2014) p.111
    Details
    Publication Date: 2017-03-16
    Description: Mariene borstelwormen vormen een ecologisch belangrijke, soortenrijke groep. Van diverse families is niet veel bekend over het voorkomen in Nederland en de bamboewormen (familie Maldanidae) behoren tot de slechtst bekende groepen. Bamboewormen danken hun naam aan de lange en aan het uiteinde verdikte segmenten. In dit artikel wordt een nieuwe bamboeworm voor Nederland besproken en een opsomming gegeven van de nu bekende inheemse soorten.
    Keywords: Polychaeta ; Maldanidae ; Micromaldane ornithochaeta ; Nederland ; herkenning ; verspreiding ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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  • 14
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    Slakkendodende vliegen van het genus Anticheta in Nederland, met twee soorten nieuw voor de fauna (Diptera: Sciomyzidae) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.42 (2014) p.47
    Details
    Publication Date: 2017-03-16
    Description: Slakkendodende vliegen zijn nog relatief slecht onderzocht in ons land, zeker de kleine soorten. De vertegenwoordigers van het genus Anticheta zijn kleine vliegjes, waarvan slechts twee soorten uit ons land bekend waren. Uitgebreider onderzoek, zowel in collecties als in het veld, heeft twee nieuwe soorten voor de fauna aan het licht gebracht: Anticheta nigra en A. obliviosa. Van de eerste soort waren wereldwijd slechts acht exemplaren bekend.
    Keywords: Diptera ; Sciomyzidae ; Anticheta ; Nederland ; herkenning ; biologie ; verspreiding ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 15
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    Het dotterbloemgitje Cheilosia frontalis nieuw voor Nederland (Diptera: Syrphidae) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.43 (2014) p.37
    Details
    Publication Date: 2017-03-16
    Description: Zelfs in een goed onderzochte insectengroep als de zweefvliegen zijn nog altijd nieuwe soorten voor de Nederlandse fauna te ontdekken. Ook in 2014 was het weer raak, dit keer in het fraaie natuurgebied rond de Drentsche Aa. Het lijkt niet toevallig dat deze aanvulling op de Nederlandse fauna juist hier werd gevonden. Deze vindplaats vult ecologische informatie uit het buitenland aan, waardoor langzamerhand een beeld begint te ontstaan van de levenswijze van deze zeldzame zweefvlieg, waarover tot voor kort weinig bekend was.
    Keywords: Diptera ; Syrphidae ; Cheilosia frontalis ; Nederland ; herkenning ; biologie ; verspreiding ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 16
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    Nieuwe vondsten van de doornkaakzandbij Andrena trimmerana in Nederland (Hymenoptera: Apoidea: Andrenidae) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.42 (2014) p.75
    Details
    Publication Date: 2017-03-16
    Description: De doornkaakzandbij ziet er in het voorjaar een beetje anders uit dan in de zomer. Daarom worden de voorjaarsdieren door sommigen tot een andere soort beschouwd dan de zomerdieren. Uit Nederland zijn slechts drie exemplaren bekend: twee uit het voorjaar en één uit de zomer. Toevallig komen alle exemplaren uit hetzelfde gebied. Of is dit geen toeval?
    Keywords: Hymenoptera ; Apoidea ; Andrenidae ; Andrena trimmerana ; Nederland ; herkenning ; verspreiding ; biologie ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 17
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    Het Sachalin-elfje Melangyna pavlovskyi nieuw voor Nederland (Diptera: Syrphidae) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.42 (2014) p.29
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    Publication Date: 2017-03-16
    Description: Elfjes behoren tot de vroegste zweefvliegen die in het voorjaar uit de pop kruipen. Rond bloeiende wilgen wemelt het vaak van wilgenelfjes Melangyna lasiophthalma, waardoor het zoeken naar de zeldzamere soorten soms lastig is. Toch zijn de meeste soorten relatief makkelijk van elkaar te onderscheiden. Met de vondst van het Sachalinelfje M. pavlovskyi wordt het echter weer iets lastiger.
    Keywords: Diptera ; Syrphidae ; Melangyna pavlovskyi ; Nederland ; herkenning ; verspreiding ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 18
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    Drie steltmuggen nieuw voor Nederland (Diptera: Limoniidae) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.42 (2014) p.19
    Details
    Publication Date: 2017-03-16
    Description: Steltmuggen lijken op langpootmuggen en zijn daar nauw aan verwant. Veel soorten zijn groot en karakteristiek gekleurd, maar toch zijn ze in Nederland nog weinig bestudeerd. Dit artikel bewijst dat er nog veel te ontdekken valt: in één jaar tijd zijn drie soorten gevonden die nog niet uit ons land bekend waren: Atypophthalmus inustus, Molophilus niger en Arctoconopa melampodia. Hiermee komt het totaal aantal soorten voor Nederland op 149. De nieuwe meldingen sluiten goed aan op het bekende verspreidingsgebied.
    Keywords: Diptera ; Limoniidae ; Nederland ; verspreiding ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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  • 19
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    De wants Jalla dumosa na 45 jaar weer in Nederland waargenomen (Heteroptera: Pentatomidae) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.43 (2014) p.9
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    Publication Date: 2017-03-16
    Description: Jalla dumosa is een in Nederland zeer zeldzame pentatomide, die in 1969 voor het laatst was waargenomen op Terschelling. Na 45 jaren zonder waarnemingen werd ze in 2014 weer in klein aantal waargenomen in de Kooiduinen op Ameland. Rupsen van onder andere de duinparelmoervlinder en de sint-jansvlinder stonden daar op het menu. In deze bijdrage wordt informatie samengevat over de vondsten in Nederland, de biologie en de verspreiding van de soort.
    Keywords: Heteroptera ; Pentatomidae ; Jalla dumosa ; Nederland ; verspreiding ; biologie ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 20
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    The exotic jellyfish Blackfordia virginica introduced into the Netherlands (Cnidaria: Hydrozoa) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.43 (2014) p.103
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    Publication Date: 2017-03-16
    Description: In August 2014 the exotic jellyfish Blackfordia virginica was captured in the harbour of Amsterdam. This is the first confirmed record of this species in the Netherlands, although in October 2013 a possible specimen was filmed and released. This indicates that the species might be established in the Amsterdam area, although repeated introduction with ballast water cannot be ruled out. In September 2014 hydrozoan polyp colonies closely resembling those of B. virginica were collected near IJmuiden in the Noordzeekanaal, a canal connecting Amsterdam with the North Sea at IJmuiden.
    Keywords: Cnidaria ; Hydrozoa ; Blackfordia virginica ; Netherlands ; exotic species ; distribution ; identification ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 21
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    Het hooiwagengenus Trogulus in Nederland (Opiliones: Trogulidae) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.42 (2014) p.1
    Details
    Publication Date: 2017-03-16
    Description: Wie een steen of boomstronk omkeert en voor het eerst een Trogulus opmerkt, zal dit bizarre beest niet direct associëren met een hooiwagen. Met de korte, stevige poten, het afgeplatte achterlijf dat overdekt is met strooisel en zand, en een trage manier van voortbewegen is het een ongewone verschijning. De soorten van dit geslacht zijn bodembewoners die zich voornamelijk voeden met kleine huisjesslakken. Uit ons land waren tot nu toe twee soorten bekend. De identiteit van een van die twee was lang onzeker, maar door nieuwe inzichten is nu duidelijk om welke soort het werkelijk gaat. In Nederland blijkt bovendien nog een derde soort voor te komen, die hier voor het eerst gemeld wordt.
    Keywords: Opiliones ; Trogulidae ; Trogulus ; Nederland ; herkenning ; verspreiding ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 22
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    De gouden stamjager Choerades igneus nieuw voor Nederland (Diptera: Asilidae) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.43 (2014) p.47
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    Publication Date: 2017-03-16
    Description: Roofvliegen zijn met 40 Nederlandse soorten een vrij kleine groep, die behoorlijk goed is onderzocht. Het gebeurt dan ook niet vaak dat er een nieuwe soort voor de Nederlandse fauna kan worden opgetekend. De meeste roofvliegen zijn grijze vliegen, zo niet de stamjagers van het genus Choerades. Dit zijn juist vrij opvallend gekleurde vliegen. Zo heeft de rode dennenstamjager Choerades gilvus een rood gekleurd achterlijf. Opmerkelijk genoeg blijkt dat in Nederland juist onder deze opvallende verschijning twee soorten schuilgaan.
    Keywords: Diptera ; Asilidae ; Choerades igneus ; Nederland ; verspreiding ; biologie ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 23
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    Bruchus brachialis, een zaadkever nieuw voor de Nederlandse fauna (Coleoptera: Chrysomelidae) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.43 (2014) p.23
    Details
    Publication Date: 2017-03-16
    Description: Onlangs werd op een braakliggend terrein in Roermond de zaadkever Bruchus brachialis verzameld. Dit is de eerste Nederlandse vondst van deze zuidelijke soort. Een reeks recente waarnemingen uit de ons omringende landen laat zien dat deze soort al enige jaren in een noordwaartse areaaluitbreiding verwikkeld is. Met deze ontdekking komt het aantal Nederlandse Bruchus-soorten op zeven.
    Keywords: Coleoptera ; Chrysomelidae ; Nederland ; herkenning ; biologie ; verspreiding ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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    De springstaart Entomobrya unostrigata nieuw voor noordwest Europa (Hexapoda: Collembola: Entomobryidae) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.42 (2014) p.63
    Details
    Publication Date: 2017-03-16
    Description: Nieuw gevormd landschap, zoals jonge duinvalleien, opgespoten polders en bedrijventerreinen in ontwikkeling vormen de habitat van gespecialiseerde soorten. Je moet tegen een stootje kunnen om in een dergelijke zandige, schaars begroeide omgeving te overleven. Vooral langdurig warme, droge perioden vormen een probleem voor vochtminnende bodemdieren. De springstaartsoorten die hier overleven zijn warmteminnend en droogteresistent, een bijzondere combinatie voor bodemdieren. Dit geldt ook voor Entomobrya unostrigata, een nieuwe aanwinst voor de fauna van Noordwest-Europa. Er is een aantal populaties van deze soort op de Tweede Maasvlakte gevonden. De dieren zaten hier onder stenen en hout op opgespoten zand.
    Keywords: Collembola ; Entomobryidae ; Entomobrya unostrigata ; Nederland ; herkenning ; verspreiding ; biologie ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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    Sigalionide zeerupsen in Nederland, met Fimbriosthenelais minor nieuw voor Nederland (Polychaeta: Sigalionidae) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.42 (2014) p.71
    Details
    Publication Date: 2017-03-16
    Description: De Polychaeta vormen een groep van vrijwel uitsluitend mariene wormen, gekenmerkt door een geleed lichaam met aan de meeste leden een tamelijk groot aantal borstels. Het is een soortenrijke groep; ze spelen een belangrijke rol in de ecologie en diversiteit van vooral zachte, maar ook harde zeebodems. In vergelijking met de kreeftachtigen en weekdieren, eveneens soortenrijke groepen in dezelfde biotoop, zijn borstelwormen minder goed onderzocht. In dit artikel wordt de zeerups Fimbriosthenelais minor nieuw voor ons land gemeld. Met name op stenige en schelprijke bodems zijn nog meer nieuwe borstelwormen voor ons land te verwachten.
    Keywords: Polychaeta ; Sigalionidae ; Fimbriosthenelais minor ; Nederland ; herkenning ; verspreiding ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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    Verspreiding en biotoop van het kalkdoorntje Tetrix tenuicornis in de Gelderse Poort (Orthoptera) (2014)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.42 (2014) p.55
    Details
    Publication Date: 2017-03-16
    Description: Het kalkdoorntje is een zeldzame sprinkhanensoort, die vooral bekend is uit Zuid-Limburg en van enkele locaties in het rivierengebied. Over het voorkomen van dit kleine sprinkhaantje binnen de Gelderse Poort was lange tijd weinig bekend. Pas vanaf 2007 worden regelmatig waarnemingen gedaan. Toevallige waarnemingen op, voor de auteur, onverwachte locaties vormden de aanleiding voor een grondige inventarisatie in de jaren 2011-2013. Hieruit komt naar voren dat het kalkdoorntje een ruime verspreiding heeft binnen de Gelderse Poort en een meer diverse biotoopkeuze heeft dan voorheen bekend was.
    Keywords: Orthoptera ; Tetrigidae ; Tetrix tenuicornis ; verspreiding ; biologie ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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    An Examination of Parameters Affecting Large Eddy Simulations of Flow Past a Square Cylinder (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Separated flow over a bluff body is analyzed via large eddy simulations. The turbulent flow around a square cylinder features a variety of complex flow phenomena such as highly unsteady vortical structures, reverse flow in the near wall region, and wake turbulence. The formation of spanwise vortices is often times artificially suppressed in computations by either insufficient depth or a coarse spanwise resolution. As the resolution is refined and the domain extended, the artificial turbulent energy exchange between spanwise and streamwise turbulence is eliminated within the wake region. A parametric study is performed highlighting the effects of spanwise vortices where the spanwise computational domain's resolution and depth are varied. For Re=22,000, the mean and turbulent statistics computed from the numerical large eddy simulations (NLES) are in good agreement with experimental data. Von-Karman shedding is observed in the wake of the cylinder. Mesh independence is illustrated by comparing a mesh resolution of 2 million to 16 million. Sensitivities to time stepping were minimized and sampling frequency sensitivities were nonpresent. While increasing the spanwise depth and resolution can be costly, this practice was found to be necessary to eliminating the artificial turbulent energy exchange.
    Keywords: Aerodynamics
    Type: AIAA Paper 2014-2089 , E-663992 , AIAA Fluid Dynamics Conference; Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States
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    Wedge Shock and Nozzle Exhaust Plume Interaction in a Supersonic Jet Flow (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Fundamental research for sonic boom reduction is needed to quantify the interaction of shock waves generated from the aircraft wing or tail surfaces with the nozzle exhaust plume. Aft body shock waves that interact with the exhaust plume contribute to the near-field pressure signature of a vehicle. The plume and shock interaction was studied using computational fluid dynamics and compared with experimental data from a coaxial convergent-divergent nozzle flow in an open jet facility. A simple diamond-shaped wedge was used to generate the shock in the outer flow to study its impact on the inner jet flow. Results show that the compression from the wedge deflects the nozzle plume and shocks form on the opposite plume boundary. The sonic boom pressure signature of the nozzle exhaust plume was modified by the presence of the wedge. Both the experimental results and computational predictions show changes in plume deflection.
    Keywords: Aerodynamics
    Type: E-663895 , AIAA SciTech 2014; Jan 13, 2014 - Jan 17, 2014; National Harbor, MD; United States
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    Dielectric Barrier Discharge (DBD) Plasma Actuators Thrust-Measurement Methodology Incorporating New Anti-Thrust Hypothesis (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: We discuss thrust measurements of Dielectric Barrier Discharge (DBD) plasma actuators devices used for aerodynamic active flow control. After a review of our experience with conventional thrust measurement and significant non-repeatability of the results, we devised a suspended actuator test setup, and now present a methodology of thrust measurements with decreased uncertainty. The methodology consists of frequency scans at constant voltages. The procedure consists of increasing the frequency in a step-wise fashion from several Hz to the maximum frequency of several kHz, followed by frequency decrease back down to the start frequency of several Hz. This sequence is performed first at the highest voltage of interest, then repeated at lower voltages. The data in the descending frequency direction is more consistent and selected for reporting. Sample results show strong dependence of thrust on humidity which also affects the consistency and fluctuations of the measurements. We also observed negative values of thrust or "anti-thrust", at low frequencies between 4 Hz and up to 64 Hz. The anti-thrust is proportional to the mean-squared voltage and is frequency independent. Departures from the parabolic anti-thrust curve are correlated with appearance of visible plasma discharges. We propose the anti-thrust hypothesis. It states that the measured thrust is a sum of plasma thrust and anti-thrust, and assumes that the anti-thrust exists at all frequencies and voltages. The anti-thrust depends on actuator geometry and materials and on the test installation. It enables the separation of the plasma thrust from the measured total thrust. This approach enables more meaningful comparisons between actuators at different installations and laboratories. The dependence on test installation was validated by surrounding the actuator with a large diameter, grounded, metal sleeve.
    Keywords: Aerodynamics
    Type: AIAA Paper 2014-0486 , E-18857-1 , AIAA SciTech 2014; Jan 13, 2014 - Jan 17, 2014; National Harbor, MD; United States
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    Validation of 3-D Ice Accretion Measurement Methodology for Experimental Aerodynamic Simulation (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Determining the adverse aerodynamic effects due to ice accretion often relies on dry-air wind-tunnel testing of artificial, or simulated, ice shapes. Recent developments in ice accretion documentation methods have yielded a laser-scanning capability that can measure highly three-dimensional features of ice accreted in icing wind tunnels. The objective of this paper was to evaluate the aerodynamic accuracy of ice-accretion simulations generated from laser-scan data. Ice-accretion tests were conducted in the NASA Icing Research Tunnel using an 18-inch chord, 2-D straight wing with NACA 23012 airfoil section. For six ice accretion cases, a 3-D laser scan was performed to document the ice geometry prior to the molding process. Aerodynamic performance testing was conducted at the University of Illinois low-speed wind tunnel at a Reynolds number of 1.8 x 10(exp 6) and a Mach number of 0.18 with an 18-inch chord NACA 23012 airfoil model that was designed to accommodate the artificial ice shapes. The ice-accretion molds were used to fabricate one set of artificial ice shapes from polyurethane castings. The laser-scan data were used to fabricate another set of artificial ice shapes using rapid prototype manufacturing such as stereolithography. The iced-airfoil results with both sets of artificial ice shapes were compared to evaluate the aerodynamic simulation accuracy of the laser-scan data. For four of the six ice-accretion cases, there was excellent agreement in the iced-airfoil aerodynamic performance between the casting and laser-scan based simulations. For example, typical differences in iced-airfoil maximum lift coefficient were less than 3% with corresponding differences in stall angle of approximately one degree or less. The aerodynamic simulation accuracy reported in this paper has demonstrated the combined accuracy of the laser-scan and rapid-prototype manufacturing approach to simulating ice accretion for a NACA 23012 airfoil. For several of the ice-accretion cases tested, the aerodynamics is known to depend upon the small, three dimensional features of the ice. These data show that the laser-scan and rapid-prototype manufacturing approach is capable of replicating these ice features within the reported accuracies of the laser-scan measurement and rapid-prototyping method; thus providing a new capability for high-fidelity ice-accretion documentation and artificial ice-shape fabrication for icing research.
    Keywords: Aerodynamics
    Type: GRC-E-DAA-TN14961 , AIAA Atmospheric and Space Environments Conference; Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States
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    Contra-Rotating Open Rotor Tone Noise Prediction (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Reliable prediction of contra-rotating open rotor (CROR) noise is an essential element of any strategy for the development of low-noise open rotor propulsion systems that can meet both the community noise regulations and the cabin noise limits. Since CROR noise spectra typically exhibits a preponderance of tones, significant efforts have been directed towards predicting their tone spectra. To that end, there has been an ongoing effort at NASA to assess various in-house open rotor tone noise prediction tools using a benchmark CROR blade set for which significant aerodynamic and acoustic data had been acquired in wind tunnel tests. In the work presented here, the focus is on the near-field noise of the benchmark open rotor blade set at the cruise condition. Using an analytical CROR tone noise model with input from high-fidelity aerodynamic simulations, detailed tone noise spectral predictions have been generated and compared with the experimental data. Comparisons indicate that the theoretical predictions are in good agreement with the data, especially for the dominant CROR tones and their overall sound pressure level. The results also indicate that, whereas individual rotor tones are well predicted by the linear sources (i.e., thickness and loading), for the interaction tones it is essential that the quadrupole sources be included in the analysis.
    Keywords: Aerodynamics
    Type: GRC-E-DAA-TN15607 , AIAA/CEAS Aeroacoustics Conference; Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States
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    Trim and Structural Optimization of Subsonic Transport Wings Using Nonconventional Aeroelastic Tailoring (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Several minimum-mass aeroelastic optimization problems are solved to evaluate the effectiveness of a variety of novel tailoring schemes for subsonic transport wings. Aeroelastic strength and panel buckling constraints are imposed across a variety of trimmed maneuver loads. Tailoring with metallic thickness variations, functionally graded materials, composite laminates, tow steering, and distributed trailing edge control effectors are all found to provide reductions in structural wing mass with varying degrees of success. The question as to whether this wing mass reduction will offset the increased manufacturing cost is left unresolved for each case.
    Keywords: Aerodynamics
    Type: NF1676L-17757 , AIAA Aviation and Aeronautics Forum and Exposition (AVIATION 2014); Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States
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    Steady and Unsteady Nozzle Simulations Using the Conservation Element and Solution Element Method (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper presents results from computational fluid dynamic (CFD) simulations of a three-stream plug nozzle. Time-accurate, Euler, quasi-1D and 2D-axisymmetric simulations were performed as part of an effort to provide a CFD-based approach to modeling nozzle dynamics. The CFD code used for the simulations is based on the space-time Conservation Element and Solution Element (CESE) method. Steady-state results were validated using the Wind-US code and a code utilizing the MacCormack method while the unsteady results were partially validated via an aeroacoustic benchmark problem. The CESE steady-state flow field solutions showed excellent agreement with solutions derived from the other methods and codes while preliminary unsteady results for the three-stream plug nozzle are also shown. Additionally, a study was performed to explore the sensitivity of gross thrust computations to the control surface definition. The results showed that most of the sensitivity while computing the gross thrust is attributed to the control surface stencil resolution and choice of stencil end points and not to the control surface definition itself.Finally, comparisons between the quasi-1D and 2D-axisymetric solutions were performed in order to gain insight on whether a quasi-1D solution can capture the steady and unsteady nozzle phenomena without the cost of a 2D-axisymmetric simulation. Initial results show that while the quasi-1D solutions are similar to the 2D-axisymmetric solutions, the inability of the quasi-1D simulations to predict two dimensional phenomena limits its accuracy.
    Keywords: Aerodynamics
    Type: GRC-E-DAA-TN16144 , AIAA Joint Propulsion Conference; Jul 28, 2014 - Jul 30, 2014; Cleveland, OH; United States
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    The Origin of Inlet Buzz in a Mach 1.7 Low Boom Inlet Design (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Supersonic inlets with external compression, having a good level performance at the critical operating point, exhibit a marked instability of the flow in some subcritical operation below a critical value of the capture mass flow ratio. This takes the form of severe oscillations of the shock system, commonly known as "buzz". The underlying purpose of this study is to indicate how Detached Eddy Simulation (DES) analysis of supersonic inlets will alter how we envision unsteady inlet aerodynamics, particularly inlet buzz. Presented in this paper is a discussion regarding the physical explanation underlying inlet buzz as indicated by DES analysis. It is the normal shock wave boundary layer separation along the spike surface which reduces the capture mass flow that is the controlling mechanism which determines the onset of inlet buzz, and it is the aerodynamic characteristics of a choked nozzle that provide the feedback mechanism that sustains the buzz cycle by imposing a fixed mean corrected inlet weight flow. Comparisons between the DES analysis of the Lockheed Martin Corporation (LMCO) N+2 inlet and schlieren photographs taken during the test of the Gulfstream Large Scale Low Boom (LSLB) inlet in the NASA 8x6 ft. Supersonic Wind Tunnel (SWT) show a strong similarity both in turbulent flow field structure and shock wave formation during the buzz cycle. This demonstrates the value of DES analysis for the design and understanding of supersonic inlets.
    Keywords: Aerodynamics
    Type: GRC-E-DAA-TN15470 , Joint Propulsion Conference; Jul 28, 2014 - Jul 30, 2014; Cleveland, OH; United States
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    Thrust Removal Scheme for the FAST-MAC Circulation Control Model Tested in the National Transonic Facility (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A second wind tunnel test of the FAST-MAC circulation control semi-span model was recently completed in the National Transonic Facility at the NASA Langley Research Center. The model allowed independent control of four circulation control plenums producing a high momentum jet from a blowing slot near the wing trailing edge that was directed over a 15% chord simple-hinged flap. The model was configured for transonic testing of the cruise configuration with 0deg flap deflection to determine the potential for drag reduction with the circulation control blowing. Encouraging results from analysis of wing surface pressures suggested that the circulation control blowing was effective in reducing the transonic drag on the configuration, however this could not be quantified until the thrust generated by the blowing slot was correctly removed from the force and moment balance data. This paper will present the thrust removal methodology used for the FAST-MAC circulation control model and describe the experimental measurements and techniques used to develop the methodology. A discussion on the impact to the force and moment data as a result of removing the thrust from the blowing slot will also be presented for the cruise configuration, where at some Mach and Reynolds number conditions, the thrust-removed corrected data showed that a drag reduction was realized as a consequence of the blowing.
    Keywords: Aerodynamics
    Type: AIAA Paper-2014-2402 , NF1676L-17629 , AIAA Applied Aerodynamics Conference; Jun 16, 2014 - Jun 20, 2014; Atlanta, GA.; United States
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    Evaluation of Linear, Inviscid, Viscous, and Reduced-Order Modeling Aeroelastic Solutions of the AGARD 445.6 Wing Using Root Locus Analysis (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Reduced-order modeling (ROM) methods are applied to the CFD-based aeroelastic analysis of the AGARD 445.6 wing in order to gain insight regarding well-known discrepancies between the aeroelastic analyses and the experimental results. The results presented include aeroelastic solutions using the inviscid CAP-TSD code and the FUN3D code (Euler and Navier-Stokes). Full CFD aeroelastic solutions and ROM aeroelastic solutions, computed at several Mach numbers, are presented in the form of root locus plots in order to better reveal the aeroelastic root migrations with increasing dynamic pressure. Important conclusions are drawn from these results including the ability of the linear CAP-TSD code to accurately predict the entire experimental flutter boundary (repeat of analyses performed in the 1980's), that the Euler solutions at supersonic conditions indicate that the third mode is always unstable, and that the FUN3D Navier-Stokes solutions stabilize the unstable third mode seen in the Euler solutions.
    Keywords: Aerodynamics
    Type: AIAA Paper 2014-0496 , NF1676-16636 , AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference; Jan 13, 2014 - Jan 17, 2014; National Harbor, MD; United States
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    Nonlinear Aeroelastic Analysis of the HIAD TPS Coupon in the NASA 8' High Temperature Tunnel: Theory and Experiment (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The purpose of this work is to develop a set of theoretical and experimental techniques to characterize the aeroelasticity of the thermal protection system (TPS) on the NASA Hypersonic Inflatable Aerodynamic Decelerator (HIAD). A square TPS coupon experiences trailing edge oscillatory behavior during experimental testing in the 8' High Temperature Tunnel (HTT), which may indicate the presence of aeroelastic flutter. Several theoretical aeroelastic models have been developed, each corresponding to a different experimental test configuration. Von Karman large deflection theory is used for the plate-like components of the TPS, along with piston theory for the aerodynamics. The constraints between the individual TPS layers and the presence of a unidirectional foundation at the back of the coupon are included by developing the necessary energy expressions and using the Rayleigh Ritz method to derive the nonlinear equations of motion. Free vibrations and limit cycle oscillations are computed and the frequencies and amplitudes are compared with accelerometer and photogrammetry data from the experiments.
    Keywords: Aerodynamics
    Type: NASA/TM-2014-218267 , L-20356 , NF1676L-18077
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    AFC-Enabled Vertical Tail System Integration Study (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: This document serves as the final report for the SMAAART AFC-Enabled Vertical Tail System Integration Study. Included are the ground rule assumptions which have gone into the study, layouts of the baseline and AFC-enabled configurations, critical sizing information, system requirements and architectures, and assumed system properties that result in an NPV assessment of the two candidate AFC technologies.
    Keywords: Aerodynamics
    Type: NASA/CR-2014-218168 , NF1676L-18162
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    Analysis of Low Speed Stall Aerodynamics of a Swept Wing with Laminar Flow Glove (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Reynolds-Averaged Navier-Stokes (RANS) computational fluid dynamics (CFD) analysis was conducted to study the low-speed stall aerodynamics of a GIII aircraft's swept wing modified with a laminar-flow wing glove. The stall aerodynamics of the gloved wing were analyzed and compared with the unmodified wing for the flight speed of 120 knots and altitude of 2300 ft above mean sea level (MSL). The Star-CCM+ polyhedral unstructured CFD code was first validated for wing stall predictions using the wing-body geometry from the First American Institute of Aeronautics and Astronautics (AIAA) CFD High-Lift Prediction Workshop. It was found that the Star-CCM+ CFD code can produce results that are within the scattering of other CFD codes considered at the workshop. In particular, the Star-CCM+ CFD code was able to predict wing stall for the AIAA wing-body geometry to within 1 degree of angle of attack as compared to benchmark wind-tunnel test data. Current results show that the addition of the laminar-flow wing glove causes the gloved wing to stall much earlier than the unmodified wing. Furthermore, the gloved wing has a different stall characteristic than the clean wing, with no sharp lift drop-off at stall for the gloved wing.
    Keywords: Aerodynamics
    Type: DFRC-E-DAA-TN13285
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    Computational Studies for Sonic Boom Prediction (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: Outline: Introduction; Launch Ascent and Vehicle Aerodynamics (LAVA) Framework; 1st AIAA Sonic Boom Prediction Workshop Oblique Shock/Plume Interaction; Summary.
    Keywords: Aerodynamics
    Type: ARC-E-DAA-TN18916 , Applied Modeling and Simulation Seminar Series; Oct 30, 2014; Moffett Field, CA; United States
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    Delay of Transition Using Forced Damping (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Several experiments which have reported a delay of transition are analyzed in terms of the frequencies of the induced disturbances generated by different flow control elements. Two of the experiments employed passive stabilizers in the boundary layer, one leading-edge bluntness, and one employed an active spark discharge in the boundary layer. It is found that the frequencies generated by the various elements lie in the damping region of the associated stability curve. It is concluded that the creation of strong disturbances in the damping region stabilizes the boundary-layer and delays the transition from laminar to turbulent flow.
    Keywords: Aerodynamics
    Type: NASA/TM-2014-218551 , L-20496 , NF1676L-20143
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    Robust, Optimal Subsonic Airfoil Shapes (2014)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: A method has been developed to create an airfoil robust enough to operate satisfactorily in different environments. This method determines a robust, optimal, subsonic airfoil shape, beginning with an arbitrary initial airfoil shape, and imposes the necessary constraints on the design. Also, this method is flexible and extendible to a larger class of requirements and changes in constraints imposed.
    Keywords: Aerodynamics
    Type: ARC-14586-2 , NASA Tech Briefs, January 2014; 22
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    Self-Contained Compressed-Flow Generation Device for Use in Making Differential Measurements (2014)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A device used in making differential measurements of a flow includes a flow obstruction and a support arm. The flow obstruction's forward portion is a nose cone. The flow obstruction's aft portion is coupled to the nose cone. The support arm's first end is coupled to an exterior wall of a conduit, and its second end is coupled to the forward portion of the flow obstruction. The support arm positions the flow obstruction in the conduit such that a flow region is defined around its nose cone, and such that the support arm's first and second end are separated from one another with respect to a length dimension of the conduit. Measurement ports are provided in the support arm and flow obstruction. Manifolds extending through the flow obstruction and support arm couple the ports to points at the exterior wall of the conduit.
    Keywords: Aerodynamics
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    Multi-Element Airfoil System (2014)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A multi-element airfoil system includes an airfoil element having a leading edge region and a skin element coupled to the airfoil element. A slat deployment system is coupled to the slat and the skin element, and is capable of deploying and retracting the slat and the skin element. The skin element substantially fills the lateral gap formed between the slat and the airfoil element when the slat is deployed. The system further includes an uncoupling device and a sensor to remove the skin element from the gap based on a critical angle-of-attack of the airfoil element. The system can alternatively comprise a trailing edge flap, where a skin element substantially fills the lateral gap between the flap and the trailing edge region of the airfoil element. In each case, the skin element fills a gap between the airfoil element and the deployed flap or slat to reduce airframe noise.
    Keywords: Aerodynamics
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    Advanced Modified High Performance Synthetic Jet Actuator with Curved Chamber (2014)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The advanced modified high performance synthetic jet actuator with optimized curvature shape chamber (ASJA-M) is a synthetic jet actuator (SJA) with a lower volume reservoir or chamber. A curved chamber is used, instead of the conventional cylinder chamber, to reduce the dead volume of the jet chamber and increase the efficiency of the synthetic jet actuator. The shape of the curvature corresponds to the maximum displacement (deformation) profile of the electroactive diaphragm. The jet velocity and mass flow rate for the ASJA-M will be several times higher than conventional piezoelectric actuators.
    Keywords: Aerodynamics
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    Aeroelastic Tailoring via Tow Steered Composites (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The use of tow steered composites, where fibers follow prescribed curvilinear paths within a laminate, can improve upon existing capabilities related to aeroelastic tailoring of wing structures, though this tailoring method has received relatively little attention in the literature. This paper demonstrates the technique for both a simple cantilevered plate in low-speed flow, as well as the wing box of a full-scale high aspect ratio transport configuration. Static aeroelastic stresses and dynamic flutter boundaries are obtained for both cases. The impact of various tailoring choices upon the aeroelastic performance is quantified: curvilinear fiber steering versus straight fiber steering, certifiable versus noncertifiable stacking sequences, a single uniform laminate per wing skin versus multiple laminates, and identical upper and lower wing skins structures versus individual tailoring.
    Keywords: Aerodynamics
    Type: NASA/TM-2014-218517 , L-20443 , NF1676L-19338
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    Aeroservoelastic Testing of Free Flying Wind Tunnel Models Part 2: A Centerline Supported Fullspan Model Tested for Gust Load Alleviation (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: This is part 2 of a two part document. Part 1 is titled: "Aeroservoelastic Testing of Free Flying Wind Tunnel Models Part 1: A Sidewall Supported Semispan Model Tested for Gust Load Alleviation and Flutter Suppression." A team comprised of the Air Force Research Laboratory (AFRL), Boeing, and the NASA Langley Research Center conducted three aeroservoelastic wind tunnel tests in the Transonic Dynamics Tunnel to demonstrate active control technologies relevant to large, flexible vehicles. In the first of these three tests, a full-span, aeroelastically scaled, wind tunnel model of a joined wing SensorCraft vehicle was mounted to a force balance to acquire a basic aerodynamic data set. In the second and third tests, the same wind tunnel model was mated to a new, two degree of freedom, beam mount. This mount allowed the full-span model to translate vertically and pitch. Trimmed flight at10 percent static margin and gust load alleviation were successfully demonstrated. The rigid body degrees of freedom required that the model be flown in the wind tunnel using an active control system. This risky mode of testing necessitated that a model arrestment system be integrated into the new mount. The safe and successful completion of these free-flying tests required the development and integration of custom hardware and software. This paper describes the many systems, software, and procedures that were developed as part of this effort. The balance and free flying wind tunnel tests will be summarized. The design of the trim and gust load alleviation control laws along with the associated results will also be discussed.
    Keywords: Aerodynamics
    Type: NASA/TP-2014-218170 , L-20321 , NF1676L-17355
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    Computational Simulations of Convergent Nozzles for the AIAA 1st Propulsion Aerodynamics Workshop (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Computational Fluid Dynamics (CFD) simulations were completed for a series of convergent nozzles in participation of the American Institute of Aeronautics and Astronautics (AIAA) 1st Propulsion Aerodynamics Workshop. The simulations were performed using the Wind-US flow solver. Discharge and thrust coefficients were computed for four axisymmetric nozzles with nozzle pressure ratios (NPR) ranging from 1.4 to 7.0. The computed discharge coefficients showed excellent agreement with available experimental data; the computed thrust coefficients captured trends observed in the experimental data, but over-predicted the thrust coefficient by 0.25 to 1.0 percent. Sonic lines were computed for cases with NPR 〉= 2.0 and agreed well with experimental data for NPR 〉= 2.5. Simulations were also performed for a 25 deg. conic nozzle bifurcated by a flat plate at NPR = 4.0. The jet plume shock structure was compared with and without the splitter plate to the experimental data. The Wind-US simulations predicted the shock structure well, though lack of grid resolution in the plume reduced the sharpness of the shock waves. Unsteady Reynolds-Averaged Navier-Stokes (URANS) simulations and Detached Eddy Simulations (DES) were performed at NPR = 1.6 for the 25 deg conic nozzle with splitter plate. The simulations predicted vortex shedding from the trailing edge of the splitter plate. However, the vortices of URANS and DES solutions appeared to dissipate earlier than observed experimentally. It is believed that a lack of grid resolution in the region of the vortex shedding may have caused the vortices to break down too soon
    Keywords: Aerodynamics
    Type: NASA/TM-2014-218329 , E-18926 , GRC-E-DAA-TN14457
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    AFC-Enabled Simplified High-Lift System Integration Study (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The primary objective of this trade study report is to explore the potential of using Active Flow Control (AFC) for achieving lighter and mechanically simpler high-lift systems for transonic commercial transport aircraft. This assessment was conducted in four steps. First, based on the Common Research Model (CRM) outer mold line (OML) definition, two high-lift concepts were developed. One concept, representative of current production-type commercial transonic transports, features leading edge slats and slotted trailing edge flaps with Fowler motion. The other CRM-based design relies on drooped leading edges and simply hinged trailing edge flaps for high-lift generation. The relative high-lift performance of these two high-lift CRM variants is established using Computational Fluid Dynamics (CFD) solutions to the Reynolds-Averaged Navier-Stokes (RANS) equations for steady flow. These CFD assessments identify the high-lift performance that needs to be recovered through AFC to have the CRM variant with the lighter and mechanically simpler high-lift system match the performance of the conventional high-lift system. Conceptual design integration studies for the AFC-enhanced high-lift systems were conducted with a NASA Environmentally Responsible Aircraft (ERA) reference configuration, the so-called ERA-0003 concept. These design trades identify AFC performance targets that need to be met to produce economically feasible ERA-0003-like concepts with lighter and mechanically simpler high-lift designs that match the performance of conventional high-lift systems. Finally, technical challenges are identified associated with the application of AFC-enabled highlift systems to modern transonic commercial transports for future technology maturation efforts.
    Keywords: Aerodynamics
    Type: NASA/CR-2014-218521 , NF1676L-19609
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    Aerodynamic Performance of a Compact, High Work-Factor Centrifugal Compressor at the Stage and Subcomponent Level (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The measured aerodynamic performance of a compact, high work factor, single-stage centrifugal compressor, comprising an impeller, diffuser, 90-bend, and exit guide vane (EGV), is reported. Performance levels are based on steady-state total-pressure and total-temperature rake and angularity-probe data acquired at key machine rating planes during recent testing at NASA Glenn Research Center. Aerodynamic performance at the stage level are reported for operation between 70 to 105 of design corrected speed, with subcomponent (impeller, diffuser, and exitguide-vane) detailed flow field measurements presented and discussed at the 100 design-speed condition. Individual component losses from measurements are compared with pre-test predictions on a limited basis.
    Keywords: Aerodynamics
    Type: GRC-E-DAA-TN16677 , AIAA/ASME/SAE/ASEE Joint Propulsion Conference; Jul 28, 2014 - Jul 30, 2014; Cleveland, OH; United States
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    In-Flight Aeroelastic Stability of the Thermal Protection System on the NASA HIAD, Part I: Linear Theory (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Conical shell theory and piston theory aerodynamics are used to study the aeroelastic stability of the thermal protection system (TPS) on the NASA Hypersonic Inflatable Aerodynamic Decelerator (HIAD). Structural models of the TPS consist of single or multiple orthotropic conical shell systems resting on several circumferential linear elastic supports. The shells in each model may have pinned (simply-supported) or elastically-supported edges. The Lagrangian is formulated in terms of the generalized coordinates for all displacements and the Rayleigh-Ritz method is used to derive the equations of motion. The natural modes of vibration and aeroelastic stability boundaries are found by calculating the eigenvalues and eigenvectors of a large coefficient matrix. When the in-flight configuration of the TPS is approximated as a single shell without elastic supports, asymmetric flutter in many circumferential waves is observed. When the elastic supports are included, the shell flutters symmetrically in zero circumferential waves. Structural damping is found to be important in this case. Aeroelastic models that consider the individual TPS layers as separate shells tend to flutter asymmetrically at high dynamic pressures relative to the single shell models. Several parameter studies also examine the effects of tension, orthotropicity, and elastic support stiffness.
    Keywords: Aerodynamics
    Type: AIAA Paper 2014-1520 , NF1676L-17623 , AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference; Jan 13, 2014 - Jan 17, 2014; National Harbor, Md; United States
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    Uncertainty Quantification and Certification Prediction of Low-Boom Supersonic Aircraft Configurations (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The primary objective of this work was to develop and demonstrate a process for accurate and efficient uncertainty quantification and certification prediction of low-boom, supersonic, transport aircraft. High-fidelity computational fluid dynamics models of multiple low-boom configurations were investigated including the Lockheed Martin SEEB-ALR body of revolution, the NASA 69 Delta Wing, and the Lockheed Martin 1021-01 configuration. A nonintrusive polynomial chaos surrogate modeling approach was used for reduced computational cost of propagating mixed, inherent (aleatory) and model-form (epistemic) uncertainty from both the computation fluid dynamics model and the near-field to ground level propagation model. A methodology has also been introduced to quantify the plausibility of a design to pass a certification under uncertainty. Results of this study include the analysis of each of the three configurations of interest under inviscid and fully turbulent flow assumptions. A comparison of the uncertainty outputs and sensitivity analyses between the configurations is also given. The results of this study illustrate the flexibility and robustness of the developed framework as a tool for uncertainty quantification and certification prediction of low-boom, supersonic aircraft.
    Keywords: Aerodynamics
    Type: NF1676L-18768 , AIAA Aviation 2014; Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States|AIAA Applied Aerodynamics Conference; Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States
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    Analysis of Numerical Simulation Database for Pressure Fluctuations Induced by High-Speed Turbulent Boundary Layers (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Direct numerical simulations (DNS) of Mach 6 turbulent boundary layer with nominal freestream Mach number of 6 and Reynolds number of Re(sub T) approximately 460 are conducted at two wall temperatures (Tw/Tr = 0.25, 0.76) to investigate the generated pressure fluctuations and their dependence on wall temperature. Simulations indicate that the influence of wall temperature on pressure fluctuations is largely limited to the near-wall region, with the characteristics of wall-pressure fluctuations showing a strong temperature dependence. Wall temperature has little influence on the propagation speed of the freestream pressure signal. The freestream radiation intensity compares well between wall-temperature cases when normalized by the local wall shear; the propagation speed of the freestream pressure signal and the orientation of the radiation wave front show little dependence on the wall temperature.
    Keywords: Aerodynamics
    Type: AIAA Paper-2014-2912 , NF1676L-17593 , AIAA Fluid Dynamics Conference; Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States|AIAA Aviation and Aeronautics Forum and Exposition (AVIATION 2014); Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States
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    Aerodynamic Investigation of Incidence Angle Effects in a Large Scale Transonic Turbine Cascade (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Aerodynamic measurements showing the effects of large incidence angle variations on an HPT turbine blade set are presented. Measurements were made in NASA's Transonic Turbine Blade Cascade Facility which has been used in previous studies to acquire detailed aerodynamic and heat transfer measurements for CFD code validation. The current study supports the development of variable-speed power turbine (VSPT) speed-change technology for the NASA Large Civil Tilt Rotor (LCTR) vehicle. In order to maintain acceptable main rotor propulsive efficiency, the VSPT operates over a nearly 50 percent speed range from takeoff to altitude cruise. This results in 50 deg or more variations in VSPT blade incidence angles. The cascade facility has the ability to operate over a wide range of Reynolds numbers and Mach numbers, but had to be modified in order to accommodate the negative incidence angle variation required by the LCTR VSPT operation. Using existing blade geometry with previously acquired aerodynamic data, the tunnel was re-baselined and the new incidence angle range was exercised. Midspan exit total pressure and flow angle measurements were obtained at seven inlet flow angles. For each inlet angle, data were obtained at five flow conditions with inlet Reynolds numbers varying from 6.8310 (exp 5) to 0.8510(exp 5) and two isentropic exit Mach numbers of 0.74 and 0.34. The midspan flowfield measurements were acquired using a three-hole pneumatic probe located in a survey plane 8.6 percent axial chord downstream of the blade trailing edge plane and covering three blade passages. Blade and endwall static pressure distributions were also acquired for each flow condition.
    Keywords: Aerodynamics
    Type: NASA/TM-2013-218070/REV1 , AIAA-2012-3879 , E-18746-1 , Joint Propulsion Conference and Exhibit; Jul 29, 2012 - Aug 01, 2012; Atlanta, GA; United States
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    Unsteady Aerodynamic Validation Experiences From the Aeroelastic Prediction Workshop (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The AIAA Aeroelastic Prediction Workshop (AePW) was held in April 2012, bringing together communities of aeroelasticians, computational fluid dynamicists and experimentalists. The extended objective was to assess the state of the art in computational aeroelastic methods as practical tools for the prediction of static and dynamic aeroelastic phenomena. As a step in this process, workshop participants analyzed unsteady aerodynamic and weakly-coupled aeroelastic cases. Forced oscillation and unforced system experiments and computations have been compared for three configurations. This paper emphasizes interpretation of the experimental data, computational results and their comparisons from the perspective of validation of unsteady system predictions. The issues examined in detail are variability introduced by input choices for the computations, post-processing, and static aeroelastic modeling. The final issue addressed is interpreting unsteady information that is present in experimental data that is assumed to be steady, and the resulting consequences on the comparison data sets.
    Keywords: Aerodynamics
    Type: AIAA Paper 2014-0203 , NF1676L-16688 , AIAA Aerospace Sciences Meeting; Jan 13, 2014 - Jan 17, 2014; National Harbor, MD; United States
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    Roll Damping Derivatives from Generalized Lifting-Surface Theory and Wind Tunnel Forced-Oscillation Tests (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Improving aerodynamic models for adverse loss-of-control conditions in flight is an area being researched under the NASA Aviation Safety Program. Aerodynamic models appropriate for loss of control conditions require a more general mathematical representation to predict nonlinear unsteady behaviors. As more general aerodynamic models are studied that include nonlinear higher order effects, the possibility of measurements that confound aerodynamic and structural responses are probable. In this study an initial step is taken to look at including structural flexibility in analysis of rigid-body forced-oscillation testing that accounts for dynamic rig, sting and balance flexibility. Because of the significant testing required and associated costs in a general study, it makes sense to capitalize on low cost analytical methods where possible, especially where structural flexibility can be accounted for by a low cost method. This paper provides an initial look at using linear lifting surface theory applied to rigid-body aircraft roll forced-oscillation tests.
    Keywords: Aerodynamics
    Type: AIAA Paper 2014-0731 , NF1676L-16685 , AIAA Science and Technology Forum and Exposition (SciTech2014); Jan 13, 2014 - Jan 17, 2014; National Harbor, MD; United States
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    Blade Displacement Predictions for the Full-Scale UH-60A Airloads Rotor (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An unsteady Reynolds-Averaged Navier-Stokes solver for unstructured grids is loosely coupled to a rotorcraft comprehensive code and used to simulate two different test conditions from a wind-tunnel test of a full-scale UH-60A rotor. Performance data and sectional airloads from the simulation are compared with corresponding tunnel data to assess the level of fidelity of the aerodynamic aspects of the simulation. The focus then turns to a comparison of the blade displacements, both rigid (blade root) and elastic. Comparisons of computed root motions are made with data from three independent measurement systems. Finally, comparisons are made between computed elastic bending and elastic twist, and the corresponding measurements obtained from a photogrammetry system. Overall the correlation between computed and measured displacements was good, especially for the root pitch and lag motions and the elastic bending deformation. The correlation of root lead-lag motion and elastic twist deformation was less favorable.
    Keywords: Aerodynamics
    Type: NF1676L-17750 , American Helicopter Society (AHS) Annual Forum; May 20, 2014 - May 22, 2014; Montreal, Quebec; Canada
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    Flight Tests of a Supersonic Natural Laminar Flow Airfoil (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A flight test campaign of a supersonic natural laminar flow airfoil has been recently completed. The test surface was an 80-inch (203 cm) chord and 40-inch (102 cm) span article mounted on the centerline store location of an F-15B airplane. The wing was designed with a leading edge sweep of effectively 0 deg to minimize boundary layer crossflow. The test article surface was coated with an insulating material to avoid significant heat transfer to and from the test article structure to maintain a quasi-adiabatic wall. An aircraft-mounted infrared camera system was used to determine boundary layer transition and the extent of laminar flow. The tests were flown up to Mach 2.0 and chord Reynolds numbers in excess of 30 million. The objectives of the tests were to determine the extent of laminar flow at high Reynolds numbers and to determine the sensitivity of the flow to disturbances. Both discrete (trip dots) and 2-D disturbances (forward-facing steps) were tested. A series of oblique shocks, of yet unknown origin, appeared on the surface, which generated sufficient crossflow to affect transition. Despite the unwanted crossflow, the airfoil performed well. The results indicate the sensitivity of the flow to the disturbances, which can translate into manufacturing tolerances, were similar to that of subsonic natural laminar flow wings.
    Keywords: Aerodynamics
    Type: DFRC-E-DAA-TN14087 , International Symposium on Flow Visualization; Jun 24, 2014 - Jun 28, 2014; Okinawa; Japan
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    Model-Invariant Hybrid LES-RANS Computation of Separated Flow Past Periodic Hills (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The requirement that physical quantities not vary with a hybrid LESRANS model's blending parameter imposes conditions on the computation that lead to better results across LES-RANS transitions. This promises to allow placement of those transitions so that LES is performed only where required by the physics, improving computational efficiency. The approach is applied to separated flow past periodic hills, where good predictions of separation-bubble size are seen due to the gradual, controlled, LES-RANS transition and the resulting enhanced near-wall eddy viscosity.
    Keywords: Aerodynamics
    Type: NF1676L-17795 , Symposium on Hybrid RANS-LES Methods; Mar 19, 2014 - Mar 21, 2014; College Station, TX; United States
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    Experimental Optimization of a Free-to-Rotate Wing for Small UAS (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper discusses an experimental investigation conducted to optimize a free-to-rotate wing for use on a small unmanned aircraft system (UAS). Although free-to-rotate wings have been used for decades on various small UAS and small manned aircraft, little is known about how to optimize these unusual wings for a specific application. The paper discusses some of the design rationale of the basic wing. In addition, three main parameters were selected for "optimization", wing camber, wing pivot location, and wing center of gravity (c.g.) location. A small apparatus was constructed to enable some simple experimental analysis of these parameters. A design-of-experiment series of tests were first conducted to discern which of the main optimization parameters were most likely to have the greatest impact on the outputs of interest, namely, some measure of "stability", some measure of the lift being generated at the neutral position, and how quickly the wing "recovers" from an upset. A second set of tests were conducted to develop a response-surface numerical representation of these outputs as functions of the three primary inputs. The response surface numerical representations are then used to develop an "optimum" within the trade space investigated. The results of the optimization are then tested experimentally to validate the predictions.
    Keywords: Aerodynamics
    Type: AIAA Paper 2014-2273 , NF1676L-17724 , AIAA Applied Aerodynamics Conference; Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States
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    Aerodynamic Effects of High Turbulence Intensity on a Variable-Speed Power-Turbine Blade with Large Incidence and Reynolds Number Variations (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The effects of high inlet turbulence intensity on the aerodynamic performance of a variable speed power turbine blade are examined over large incidence and Reynolds number ranges. These results are compared to previous measurements made in a low turbulence environment. Both high and low turbulence studies were conducted in the NASA Glenn Research Center Transonic Turbine Blade Cascade Facility. The purpose of the low inlet turbulence study was to examine the transitional flow effects that are anticipated at cruise Reynolds numbers. The current study extends this to LPT-relevant turbulence levels while perhaps sacrificing transitional flow effects. Assessing the effects of turbulence at these large incidence and Reynolds number variations complements the existing database. Downstream total pressure and exit angle data were acquired for 10 incidence angles ranging from +15.8deg to 51.0deg. For each incidence angle, data were obtained at five flow conditions with the exit Reynolds number ranging from 2.1210(exp 5) to 2.1210(exp 6) and at a design exit Mach number of 0.72. In order to achieve the lowest Reynolds number, the exit Mach number was reduced to 0.35 due to facility constraints. The inlet turbulence intensity, Tu, was measured using a single-wire hotwire located 0.415 axial-chord upstream of the blade row. The inlet turbulence levels ranged from 8 to 15 percent for the current study. Tu measurements were also made farther upstream so that turbulence decay rates could be calculated as needed for computational inlet boundary conditions. Downstream flow field measurements were obtained using a pneumatic five-hole pitch/yaw probe located in a survey plane 7 percent axial chord aft of the blade trailing edge and covering three blade passages. Blade and endwall static pressures were acquired for each flow condition as well. The blade loading data show that the suction surface separation that was evident at many of the low Tu conditions has been eliminated. At the extreme positive and negative incidence angles, the data show substantial differences in the exit flow field. These differences are attributable to both the higher inlet Tu directly and to the thinner inlet endwall boundary layer that the turbulence grid imposes.
    Keywords: Aerodynamics
    Type: E-18952 , AIAA Joint Propulsion Conference; Jul 28, 2014 - Jul 30, 2014; Cleveland, OH; United States
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    Tone and Broadband Noise Separation from Acoustic Data of a Scale-Model Contra-Rotating Open Rotor (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Renewed interest in contra-rotating open rotor technology for aircraft propulsion application has prompted the development of advanced diagnostic tools for better design and improved acoustical performance. In particular, the determination of tonal and broadband components of open rotor acoustic spectra is essential for properly assessing the noise control parameters and also for validating the open rotor noise simulation codes. The technique of phase averaging has been employed to separate the tone and broadband components from a single rotor, but this method does not work for the two-shaft contra-rotating open rotor. A new signal processing technique was recently developed to process the contra-rotating open rotor acoustic data. The technique was first tested using acoustic data taken of a hobby aircraft open rotor propeller, and reported previously. The intent of the present work is to verify and validate the applicability of the new technique to a realistic one-fifth scale open rotor model which has 12 forward and 10 aft contra-rotating blades operating at realistic forward flight Mach numbers and tip speeds. The results and discussions of that study are presented in this paper.
    Keywords: Aerodynamics
    Type: GRC-E-DAA-TN15182 , AIAA Aeroacoustics Conference; Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States
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    Aerodynamic Effects of High Turbulence Intensity on a Variable-Speed Power-Turbine Blade With Large Incidence and Reynolds Number Variations (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The effects of high inlet turbulence intensity on the aerodynamic performance of a variable speed power turbine blade are examined over large incidence and Reynolds number ranges. These results are compared to previous measurements made in a low turbulence environment. Both high and low turbulence studies were conducted in the NASA Glenn Research Center Transonic Turbine Blade Cascade Facility. The purpose of the low inlet turbulence study was to examine the transitional flow effects that are anticipated at cruise Reynolds numbers. The current study extends this to LPT-relevant turbulence levels while perhaps sacrificing transitional flow effects. Assessing the effects of turbulence at these large incidence and Reynolds number variations complements the existing database. Downstream total pressure and exit angle data were acquired for 10 incidence angles ranging from +15.8deg to 51.0deg. For each incidence angle, data were obtained at five flow conditions with the exit Reynolds number ranging from 2.1210(exp 5) to 2.1210(exp 6) and at a design exit Mach number of 0.72. In order to achieve the lowest Reynolds number, the exit Mach number was reduced to 0.35 due to facility constraints. The inlet turbulence intensity, Tu, was measured using a single-wire hotwire located 0.415 axial-chord upstream of the blade row. The inlet turbulence levels ranged from 8 to 15 percent for the current study. Tu measurements were also made farther upstream so that turbulence decay rates could be calculated as needed for computational inlet boundary conditions. Downstream flow field measurements were obtained using a pneumatic five-hole pitch/yaw probe located in a survey plane 7 percent axial chord aft of the blade trailing edge and covering three blade passages. Blade and endwall static pressures were acquired for each flow condition as well. The blade loading data show that the suction surface separation that was evident at many of the low Tu conditions has been eliminated. At the extreme positive and negative incidence angles, the data show substantial differences in the exit flow field. These differences are attributable to both the higher inlet Tu directly and to the thinner inlet endwall boundary layer that the turbulence grid imposes.
    Keywords: Aerodynamics
    Type: NASA/TM-2014-218137 , E-18952-1 , AIAA Joint Propulsion Conference; Jul 28, 2014 - Jul 30, 2014; Cleveland, OH; United States
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    Wind Tunnel Testing of a 120th Scale Large Civil Tilt-Rotor Model in Airplane and Helicopter Modes (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: In April 2012 and October 2013, NASA and the U.S. Army jointly conducted a wind tunnel test program examining two notional large tilt rotor designs: NASA's Large Civil Tilt Rotor and the Army's High Efficiency Tilt Rotor. The approximately 6%-scale airframe models (unpowered) were tested without rotors in the U.S. Army 7- by 10-foot wind tunnel at NASA Ames Research Center. Measurements of all six forces and moments acting on the airframe were taken using the wind tunnel scale system. In addition to force and moment measurements, flow visualization using tufts, infrared thermography and oil flow were used to identify flow trajectories, boundary layer transition and areas of flow separation. The purpose of this test was to collect data for the validation of computational fluid dynamics tools, for the development of flight dynamics simulation models, and to validate performance predictions made during conceptual design. This paper focuses on the results for the Large Civil Tilt Rotor model in an airplane mode configuration up to 200 knots of wind tunnel speed. Results are presented with the full airframe model with various wing tip and nacelle configurations, and for a wing-only case also with various wing tip and nacelle configurations. Key results show that the addition of a wing extension outboard of the nacelles produces a significant increase in the lift-to-drag ratio, and interestingly decreases the drag compared to the case where the wing extension is not present. The drag decrease is likely due to complex aerodynamic interactions between the nacelle and wing extension that results in a significant drag benefit.
    Keywords: Aerodynamics
    Type: ARC-E-DAA-TN12608 , Decennial AHS Aeromechanics Specialists'' Conference; Jan 22, 2014 - Jan 24, 2014; San Francisco, CA; United States
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    Experimental Study of Slat Noise from 30P30N Three-Element High-Lift Airfoil in JAXA Hard-Wall Low-Speed Wind Tunnel (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Aeroacoustic measurements associated with noise radiation from the leading edge slat of the canonical, unswept 30P30N three-element high-lift airfoil configuration have been obtained in a 2 m x 2 m hard-wall wind tunnel at the Japan Aerospace Exploration Agency (JAXA). Performed as part of a collaborative effort on airframe noise between JAXA and the National Aeronautics and Space Administration (NASA), the model geometry and majority of instrumentation details are identical to a NASA model with the exception of a larger span. For an angle of attack up to 10 degrees, the mean surface Cp distributions agree well with free-air computational fluid dynamics predictions corresponding to a corrected angle of attack. After employing suitable acoustic treatment for the brackets and end-wall effects, an approximately 2D noise source map is obtained from microphone array measurements, thus supporting the feasibility of generating a measurement database that can be used for comparison with free-air numerical simulations. Both surface pressure spectra obtained via KuliteTM transducers and the acoustic spectra derived from microphone array measurements display a mixture of a broad band component and narrow-band peaks (NBPs), both of which are most intense at the lower angles of attack and become progressively weaker as the angle of attack is increased. The NBPs exhibit a substantially higher spanwise coherence in comparison to the broadband portion of the spectrum and, hence, confirm the trends observed in previous numerical simulations. Somewhat surprisingly, measurements show that the presence of trip dots between the stagnation point and slat cusp enhances the NBP levels rather than mitigating them as found in a previous experiment.
    Keywords: Aerodynamics
    Type: AIAA Paper 2014-2080 , NF1676L-18887 , AIAA Aviation and Aeronautics Forum and Exposition (AVIATION 2014); Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States
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    Thrust Measurement of Dielectric Barrier Discharge (DBD) Plasma Actuators: New Anti-Thrust Hypothesis, Frequency Sweeps Methodology, Humidity and Enclosure Effects (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: We discuss thrust measurements of Dielectric Barrier Discharge (DBD) plasma actuators devices used for aerodynamic active flow control. After a review of our experience with conventional thrust measurement and significant non-repeatability of the results, we devised a suspended actuator test setup, and now present a methodology of thrust measurements with decreased uncertainty. The methodology consists of frequency scans at constant voltages. The procedure consists of increasing the frequency in a step-wise fashion from several Hz to the maximum frequency of several kHz, followed by frequency decrease back down to the start frequency of several Hz. This sequence is performed first at the highest voltage of interest, then repeated at lower voltages. The data in the descending frequency direction is more consistent and selected for reporting. Sample results show strong dependence of thrust on humidity which also affects the consistency and fluctuations of the measurements. We also observed negative values of thrust, or "anti-thrust", at low frequencies between 4 Hz and up to 64 Hz. The anti-thrust is proportional to the mean-squared voltage and is frequency independent. Departures from the parabolic anti-thrust curve are correlated with appearance of visible plasma discharges. We propose the anti-thrust hypothesis. It states that the measured thrust is a sum of plasma thrust and anti-thrust, and assumes that the anti-thrust exists at all frequencies and voltages. The anti-thrust depends on actuator geometry and materials and on the test installation. It enables the separation of the plasma thrust from the measured total thrust. This approach enables more meaningful comparisons between actuators at different installations and laboratories. The dependence on test installation was validated by surrounding the actuator with a grounded large-diameter metal sleeve. Strong dependence on humidity is also shown; the thrust significantly increased with decreasing humidity, e.g., 44 percent increase as relative humidity changed from 18 percent and dew point 33 degF to 50 percent and dew point of 57 degF.
    Keywords: Aerodynamics
    Type: NASA/TM2014-218115 , AIAA Paper 2014-0486 , E-18857 , SciTech 2014 Aerospace Sciences Meeting; Jan 13, 2014 - Jan 17, 2014; National Harbor, MD; United States
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    Static Aeroelastic and Longitudinal Trim Model of Flexible Wing Aircraft Using Finite-Element Vortex-Lattice Coupled Solution (2014)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: This paper presents a static aeroelastic model and longitudinal trim model for the analysis of a flexible wing transport aircraft. The static aeroelastic model is built using a structural model based on finite-element modeling and coupled to an aerodynamic model that uses vortex-lattice solution. An automatic geometry generation tool is used to close the loop between the structural and aerodynamic models. The aeroelastic model is extended for the development of a three degree-of-freedom longitudinal trim model for an aircraft with flexible wings. The resulting flexible aircraft longitudinal trim model is used to simultaneously compute the static aeroelastic shape for the aircraft model and the longitudinal state inputs to maintain an aircraft trim state. The framework is applied to an aircraft model based on the NASA Generic Transport Model (GTM) with wing structures allowed to flexibly deformed referred to as the Elastically Shaped Aircraft Concept (ESAC). The ESAC wing mass and stiffness properties are based on a baseline "stiff" values representative of current generation transport aircraft.
    Keywords: Aerodynamics
    Type: ARC-E-DAA-TN12487 , SciTech 2014; Jan 13, 2014 - Jan 17, 2014; Baltimore, MD; United States
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    Maintaining Aura's Orbit Requirements Under New Maneuver Operations (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Earth Observing System (EOS) Afternoon Constellation consists of five member missions (GCOM-W1, Aqua, CALIPSO, CloudSat, and Aura), each of which maintain a frozen, sun-synchronous orbit with a 16-day repeating ground track that follows the Worldwide Reference System-2 (WRS-2). Under nominal science operations for Aura, the propulsion system is oriented such that the resultant thrust vector is aligned 13.493 degrees away from the velocity vector along the yaw axis. When performing orbit maintenance maneuvers, the spacecraft performs a yaw slew to align the thrust vector in the appropriate direction. A new Drag Make Up (DMU) maneuver operations scheme has been implemented for Aura alleviating the need for the 13.493 degree yaw slew. The focus of this investigation is to assess the impact that no-slew DMU maneuver operations will have on Auras Mean Local Time (MLT) which drives the required along track separation between Aura and the constellation members, as well as Auras frozen orbit properties, eccentricity and argument of perigee. Seven maneuver strategies were analyzed to determine the best operational approach. A mirror pole strategy, with maneuvers alternating at the North and South poles, was implemented operationally to minimize impact to the MLT. Additional analysis determined that the mirror pole strategy could be further modified to include frozen orbit maneuvers and thus maintain both MLT and the frozen orbit properties under no-slew operations
    Keywords: Aerodynamics
    Type: GSFC-E-DAA-TN14703 , International Symposium on Space Flight Dynamics; May 05, 2014 - May 09, 2014; Laurel, MD; United States
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    Optimal Topology of Aircraft Rib and Spar Structures under Aeroelastic Loads (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Several topology optimization problems are conducted within the ribs and spars of a wing box. It is desired to locate the best position of lightening holes, truss/cross-bracing, etc. A variety of aeroelastic metrics are isolated for each of these problems: elastic wing compliance under trim loads and taxi loads, stress distribution, and crushing loads. Aileron effectiveness under a constant roll rate is considered, as are dynamic metrics: natural vibration frequency and flutter. This approach helps uncover the relationship between topology and aeroelasticity in subsonic transport wings, and can therefore aid in understanding the complex aircraft design process which must eventually consider all these metrics and load cases simultaneously.
    Keywords: Aerodynamics
    Type: AIAA Paper 2014-0633 , NF1676L-16611 , AIAA Multidisciplinary Design Optimization Specialist Conference; Jan 13, 2014 - Jan 17, 2014; National Harbor,MD; United States
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    Time-Spectral Rotorcraft Simulations on Overset Grids (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Time-Spectral method is derived as a Fourier collocation scheme and applied to NASA's overset Reynolds-averaged Navier-Stokes (RANS) solver OVERFLOW. The paper outlines the Time-Spectral OVERFLOWimplementation. Successful low-speed laminar plunging NACA 0012 airfoil simulations demonstrate the capability of the Time-Spectral method to resolve the highly-vortical wakes typical of more expensive three-dimensional rotorcraft configurations. Dealiasing, in the form of spectral vanishing viscosity (SVV), facilitates the convergence of Time-Spectral calculations of high-frequency flows. Finally, simulations of the isolated V-22 Osprey tiltrotor for both hover and forward (edgewise) flight validate the three-dimensional Time-Spectral OVERFLOW implementation. The Time-Spectral hover simulation matches the time-accurate calculation using a single harmonic. Significantly more temporal modes and SVV are required to accurately compute the forward flight case because of its more active, high-frequency wake.
    Keywords: Aerodynamics
    Type: ARC-E-DAA-TN15492 , Applied Aerodynamics Conference; Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States
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    Assessment of Higher-Order RANS Closures in a Decelerated Planar Wall-Bounded Turbulent Flow (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A reference DNS database is presented, which includes third- and fourth-order moment budgets for unstrained and strained planar channel flow. Existing RANS closure models for third- and fourth-order terms are surveyed, and new model ideas are introduced. The various models are then compared with the DNS data term by term using a priori testing of the higher-order budgets of turbulence transport, velocity-pressure-gradient, and dissipation for both the unstrained and strained databases. Generally, the models for the velocity-pressure-gradient terms are most in need of improvement.
    Keywords: Aerodynamics
    Type: NF1676L-17686 , (AVIATION 2014) AIAA Aviation and Aeronautics Forum and Exposition; Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States
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    Aerodynamic Effects of Turbulence Intensity on a Variable-Speed Power-Turbine Blade with Large Incidence and Reynolds Number Variations (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The effects of inlet turbulence intensity on the aerodynamic performance of a variable speed power turbine blade are examined over large incidence and Reynolds number ranges. Both high and low turbulence studies were conducted in the NASA Glenn Research Center Transonic Turbine Blade Cascade Facility. The purpose of the low inlet turbulence study was to examine the transitional flow effects that are anticipated at cruise Reynolds numbers. The high turbulence study extends this to LPT-relevant turbulence levels while perhaps sacrificing transitional flow effects. Downstream total pressure and exit angle data were acquired for ten incidence angles ranging from +15.8 to 51.0. For each incidence angle, data were obtained at five flow conditions with the exit Reynolds number ranging from 2.12105 to 2.12106 and at a design exit Mach number of 0.72. In order to achieve the lowest Reynolds number, the exit Mach number was reduced to 0.35 due to facility constraints. The inlet turbulence intensity, Tu, was measured using a single-wire hotwire located 0.415 axial-chord upstream of the blade row. The inlet turbulence levels ranged from 0.25 - 0.4 for the low Tu tests and 8- 15 for the high Tu study. Tu measurements were also made farther upstream so that turbulence decay rates could be calculated as needed for computational inlet boundary conditions. Downstream flow field measurements were obtained using a pneumatic five-hole pitchyaw probe located in a survey plane 7 axial chord aft of the blade trailing edge and covering three blade passages. Blade and endwall static pressures were acquired for each flow condition as well. The blade loading data show that the suction surface separation that was evident at many of the low Tu conditions has been eliminated. At the extreme positive and negative incidence angles, the data show substantial differences in the exit flow field. These differences are attributable to both the higher inlet Tu directly and to the thinner inlet endwall boundary layer that the turbulence grid imposes.
    Keywords: Aerodynamics
    Type: GRC-E-DAA-TN17526 , Turbine Engine Technical Symposium 2014; Sep 08, 2014 - Sep 11, 2014; Dayton, OH; United States
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    Numerical Simulations For the F-16XL Aircraft Configuration (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Numerical simulations of flow around the F-16XL are presented as a contribution to the Cranked Arrow Wing Aerodynamic Project International II (CAWAPI-II). The NASA Tetrahedral Unstructured Software System (TetrUSS) is used to perform numerical simulations. This CFD suite, developed and maintained by NASA Langley Research Center, includes an unstructured grid generation program called VGRID, a postprocessor named POSTGRID, and the flow solver USM3D. The CRISP CFD package is utilized to provide error estimates and grid adaption for verification of USM3D results. A subsonic high angle-of-attack case flight condition (FC) 25 is computed and analyzed. Three turbulence models are used in the calculations: the one-equation Spalart-Allmaras (SA), the two-equation shear stress transport (SST) and the k turbulence models. Computational results, and surface static pressure profiles are presented and compared with flight data. Solution verification is performed using formal grid refinement studies, the solution of Error Transport Equations, and adaptive mesh refinement. The current study shows that the USM3D solver coupled with CRISP CFD can be used in an engineering environment in predicting vortex-flow physics on a complex configuration at flight Reynolds numbers.
    Keywords: Aerodynamics
    Type: AIAA Paper 2014-0756 , NF1676L-16701 , AIAA Aerospace Sciences Meeting; Jan 13, 2014 - Jan 17, 2014; National Harbor, MD; United States
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    The NASA High Speed ASE Project: Computational Analyses of a Low-Boom Supersonic Configuration (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A summary of NASA's High Speed Aeroservoelasticity (ASE) project is provided with a focus on a low-boom supersonic configuration developed by Lockheed-Martin and referred to as the N+2 configuration. The summary includes details of the computational models developed to date including a linear finite element model (FEM), linear unsteady aerodynamic models, structured and unstructured CFD grids, and discussion of the FEM development including sizing and structural constraints applied to the N+2 configuration. Linear results obtained to date include linear mode shapes and linear flutter boundaries. In addition to the tasks associated with the N+2 configuration, a summary of the work involving the development of AeroPropulsoServoElasticity (APSE) models is also discussed.
    Keywords: Aerodynamics
    Type: AIAA Paper 2014-0675 , NF1676L-16637 , AIAA Aerospace Sciences Meeting; Jan 13, 2014 - Jan 17, 2014; National Harbor, MD; United States
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    A Summary of Revisions Applied to a Turbulence Response Analysis Method for Flexible Aircraft Configurations (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A software program and associated methodology to study gust loading on aircraft exists for a classification of geometrically simplified flexible configurations. This program consists of a simple aircraft response model with two rigid and three flexible symmetric degrees-of - freedom and allows for the calculation of various airplane responses due to a discrete one-minus- cosine gust as well as continuous turbulence. Simplifications, assumptions, and opportunities for potential improvements pertaining to the existing software program are first identified, then a revised version of the original software tool is developed with improved methodology to include more complex geometries, additional excitation cases, and additional output data so as to provide a more useful and precise tool for gust load analysis. In order to improve the original software program to enhance usefulness, a wing control surface and horizontal tail control surface is added, an extended application of the discrete one-minus-cosine gust input is employed, a supplemental continuous turbulence spectrum is implemented, and a capability to animate the total vehicle deformation response to gust inputs is included. These revisions and enhancements are implemented and an analysis of the results is used to validate the modifications.
    Keywords: Aerodynamics
    Type: AIAA Paper 2014-0600 , NF1676L-16647 , AIAA Guidance, Navigation, and Control Conference; Jan 13, 2014 - Jan 17, 2014; National Harbor, MD; United States
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    An Experimntal Investigation of the 30P30N Multi-Element High-Lift Airfoil (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: High-lift devices often generate an unsteady flow field producing both broadband and tonal noise which radiates from the aircraft. In particular, the leading edge slat is often a dominant contributor to the noise signature. An experimental study of a simplified unswept high-lift configuration, the 30P30N, has been conducted to understand and identify the various flow-induced noise sources around the slat. Closed-wall wind tunnel tests are performed in the Florida State Aeroacoustic Tunnel (FSAT) to characterize the slat cove flow field using a combination of surface and off-body measurements. Mean surface pressures compare well with numerical predictions for the free-air configuration. Consistent with previous measurements and computations for 2D high-lift configurations, the frequency spectra of unsteady surface pressures on the slat surface display several narrowband peaks that decrease in strength as the angle of attack is increased. At positive angles of attack, there are four prominent peaks. The three higher frequency peaks correspond, approximately, to a harmonic sequence related to a feedback resonance involving unstable disturbances in the slat cove shear layer. The Strouhal numbers associated with these three peaks are nearly insensitive to the range of flow speeds (41-58 m/s) and the angles of attack tested (3-8.5 degrees). The first narrow-band peak has an order of magnitude lower frequency than the remaining peaks and displays noticeable sensitivity to the angle of attack. Stereoscopic particle image velocimetry (SPIV) measurements provide supplementary information about the shear layer characteristics and turbulence statistics that may be used for validating numerical simulations.
    Keywords: Aerodynamics
    Type: AIAA Paper 2014-3062 , NF1676L-18896 , AIAA Aviation and Aeronautics Forum and Exposition (AVIATION 2014); Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States
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    Space Launch System Ascent Static Aerodynamic Database Development (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes the wind tunnel testing work and data analysis required to characterize the static aerodynamic environment of NASA's Space Launch System (SLS) ascent portion of flight. Scaled models of the SLS have been tested in transonic and supersonic wind tunnels to gather the high fidelity data that is used to build aerodynamic databases. A detailed description of the wind tunnel test that was conducted to produce the latest version of the database is presented, and a representative set of aerodynamic data is shown. The wind tunnel data quality remains very high, however some concerns with wall interference effects through transonic Mach numbers are also discussed. Post-processing and analysis of the wind tunnel dataset are crucial for the development of a formal ascent aerodynamics database.
    Keywords: Aerodynamics
    Type: AIAA Paper-2014-1254 , NF1676L-17910 , AIAA Aerospace Sciences Meeting; Jan 13, 2014 - Jan 17, 2014; National Harbor, MD; United States
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    Aerodynamic Measurements of a Variable-Speed Power-Turbine Blade Section in a Transonic Turbine Cascade (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The purpose of this thesis is to document the impact of incidence angle and Reynolds number variations on the three-dimensional flow field and midspan loss and turning of a two-dimensional section of a variable-speed power-turbine (VSPT) rotor blade. Aerodynamic measurements were obtained in a transonic linear cascade at NASA Glenn Research Center in Cleveland, Ohio. Steady-state data were obtained for 10 incidence angles ranging from +15.8deg to -51.0deg. At each angle, data were acquired at five flow conditions with the exit Reynolds number (based on axial chord) varying over an order-of-magnitude from 2.12105 to 2.12106. Data were obtained at the design exit Mach number of 0.72 and at a reduced exit Mach number of 0.35 as required to achieve the lowest Reynolds number. Midspan tota lpressure and exit flow angle data were acquired using a five-hole pitch/yaw probe surveyed on a plane located 7.0 percent axial-chord downstream of the blade trailing edge plane. The survey spanned three blade passages. Additionally, three-dimensional half-span flow fields were examined with additional probe survey data acquired at 26 span locations for two key incidence angles of +5.8deg and -36.7deg. Survey data near the endwall were acquired with a three-hole boundary-layer probe. The data were integrated to determine average exit total-pressure and flow angle as functions of incidence and flow conditions. The data set also includes blade static pressures measured on four spanwise planes and endwall static pressures.
    Keywords: Aerodynamics
    Type: NASA/TM-2014-218133 , E-18929
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    A Modular Approach to Model Oscillating Control Surfaces Using Navier Stokes Equations (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-19
    Description: The use of active controls for rotorcraft is becoming more important for modern aerospace configurations. Efforts to reduce the vibrations of helicopter blades with use of active-controls are in progress. Modeling oscillating control surfaces using the linear aerodynamics theory is well established. However, higher-fidelity methods are needed to account for nonlinear effects, such as those that occur in transonic flow. The aeroelastic responses of a wing with an oscillating control surface, computed using the transonic small perturbation (TSP) theory, have been shown to cause important transonic flow effects such as a reversal of control surface effectiveness that occurs as the shock wave crosses the hinge line. In order to account for flow complexities such as blade-vortex interactions of rotor blades higher-fidelity methods based on the Navier-Stokes equations are used. Reference 6 presents a procedure that uses the Navier-Stokes equations with moving-sheared grids and demonstrates up to 8 degrees of control-surface amplitude, using a single grid. Later, this procedure was extended to accommodate larger amplitudes, based on sliding grid zones. The sheared grid method implemented in EulerlNavier-Stokes-based aeroelastic code ENS AERO was successfully applied to active control design by industry. Recently there are several papers that present results for oscillating control surface using Reynolds Averaged Navier-Stokes (RANS) equations. References 9 and 10 report 2-D cases by filling gaps with overset grids. Reference 9 compares integrated forces with the experiment at low oscillating frequencies whereas Ref. 10 reports parametric studies but with no validation. Reference II reports results for a 3D case by modeling the gap region with a deformed grid and compares force results with the experiment only at the mid-span of flap. In Ref. II grid is deformed to match the control surface deflections at the section where the measurements are made. However, there is no indication in Ref. II that the gaps are explicitly modeled as in Ref. 6. Computations using overset grids are reported in Ref. 12 for a case by adding moving control surface to an existing blade but with no validation either with an experiment or another computation.
    Keywords: Aerodynamics
    Type: ARC-E-DAA-TN12352 , Decennial AHS Aeromechanics Specialists Meeting; Jan 22, 2014 - Jan 24, 2014; San Francisco, CA; United States
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    Sensitivities of marine macrozoobenthos to environmental pressures in the Netherlands (2013)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.41 (2013) p.79
    Details
    Publication Date: 2015-12-09
    Description: The relative sensitivities of 309 common invertebrate species in Dutch marine waters are presented for environmental and anthropogenic pressures like organic enrichment, sedimentation and fisheries. The species were furthermore appointed to trophic groups like suspension and deposit feeders. The Dutch Ministry of Infrastructure and the Environment uses these data when calculating the Benthic Ecosystem Quality Index 2 and the Infaunal Trophic Index. These metrics aid in the mandatory monitoring of ecological quality for example for the European Water Framework Directive. The common Dutch species were selected based on their abundance according to, 1. the mwtl dataset including results of on-going monitoring programs issued by the Ministry, 2. the monitoring by volunteer scuba-divers for the anemoon Foundation and 3. the monitoring of fouling plates for the project setl.
    Keywords: macrozoobenthos ; marine ; Netherlands ; environment ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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    De zeepissebed Uromunna spec, de eerste waarneming van de familie Munnidae in Nederland (Isopoda) (2013)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.41 (2013) p.43
    Details
    Publication Date: 2015-12-09
    Description: Onze fauna verandert en de mariene fauna is daarop geen uitzondering. Zuidelijke soorten koloniseren onze kustwateren en exotische soorten worden door de mens aangevoerd. Voor sommige soorten is niet duidelijk waarom ze hier opduiken. De sterk veranderende kustbiotopen spelen ongetwijfeld eveneens een rol. Een niet-aflatende stroom onverwachte soorten, soms zelfs behorend tot nieuwe genera en zelfs families maken faunistisch onderzoek in de kustwateren verrassend en boeiend. In het kader van een inventarisatie van kreeftachtigen in het Deltagebied werden in de Oosterschelde bij Zierikzee verscheidene kleine monsters genomen van diverse substraten. De monsters van roodwieren bevatten een aantal opmerkelijke soorten. Dit artikel behandelt Uromunna spec., een zeepissebeddensoort van een familie die in ons land nog niet was aangetroffen.
    Keywords: Isopoda ; Munnidae ; Nederland ; Uromunna ; verspreiding ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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    First record of a settled stomatopod Platysquilla eusebia in the North Sea (Malacostraca: Stomatopoda) (2013)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.41 (2013) p.31
    Details
    Publication Date: 2015-12-09
    Description: This paper describes the discovery of a settled juvenile specimen of the stomatopod Platysquilla eusebia on the Dutch part of the Dogger Bank in the central North Sea. This is the northernmost record in Europe. The species is native to the Mediterranean and to the Atlantic coast from Portugal up to France. Further investigations have to show if the species already forms populations this far north. As the planktonic stages of P. eusebia have already been recorded in prior years, the establishment of the species should not be a problem, providing the circumstances are favourable.
    Keywords: Malacostraca ; Stomatopoda ; Platysquilla eusebia ; distribution ; Netherlands ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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    De springstaart Fasciosminthurus quinquefasciatus nieuw voor de Nederlandse fauna (Collembola: Bourletiellidae) (2013)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.40 (2013) p.1
    Details
    Publication Date: 2015-12-09
    Description: Met enige regelmaat duiken nieuwe springstaartsoorten op in ons land. Het vinden van een nieuwe soort is soms op toeval gebaseerd. Op een foto van een sprinkhaan was naast de linker voorpoot een klein, donker vlekje te zien. Uitvergroot bleek het om een klein springstaartje te gaan. Het zwart-wit gestreepte patroon liet geen ruimte voor twijfel over de determinatie: Fasciosminthurus quinquefasciatus, een nieuwe springstaart voor de Nederlandse fauna. In dit artikel wordt het genus en de soort voorgesteld, beschrijven we de habitat en geven we informatie over de verspreiding in de rest van Europa.
    Keywords: Collembola ; Bourletiellidae ; Fasciosminthurus quinquefasciatus ; Nederland ; verspreiding ; herkenning ; biologie ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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  • 84
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    Duistere heiderouwzwever Exoprosopa cleomene duikt op in Nederlandse wolzwevercollectie (Diptera: Bombyliidae) (2013)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.39 (2013) p.49
    Details
    Publication Date: 2015-12-09
    Description: De roodbruine heiderouwzwever Exoprosopa capucina is een fraaie en karakteristieke koffiebruine verschijning op de Nederlandse heideterreinen. Zoals veel wolzwevers is deze te herkennen aan de vleugeltekening en de kleur van de lichaamsbeharing. Echter naarmate de dieren ouder worden verliezen ze deze beharing en wordt de determinatie lastiger. Vermoedelijk heeft het verfomfaaide uiterlijk van een vrouwtje Exoprosopa cleomene er voor gezorgd dat deze ruim 50 jaar onopgemerkt tussen de exemplaren van E. capucina heeft gestaan.
    Keywords: Diptera ; Bombyliidae ; Exoprosopa cleomene ; Nederland ; verspreiding ; herkenning ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 85
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    Sulcacis bidentulus, een nieuwe houtzwamkever voor de Nederlandse fauna (Coleoptera: Ciidae) (2013)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.39 (2013) p.7
    Details
    Publication Date: 2015-12-09
    Description: In de afgelopen jaren werd op verschillende plekken in Nederland een houtzwamkever gevonden die tot nu toe niet officieel gemeld werd: Sulcacis bidentulus. Deze soort valt binnen de zeer eenvormige familie Ciidae op door de kleur van de dekschilden, die duidelijk iets lichter bruin zijn dan de rest van het lichaam. De soort zou zich ontwikkelen in de bleke borstelkurkzwam, die voornamelijk op populieren groeit. Oudere vondsten ontbreken en de ontdekking van deze soort op meerdere locaties duidt op een recente vestiging in ons land. Dit sluit aan bij de geconstateerde uitbreiding in Midden-Europa.
    Keywords: Coleoptera ; Ciidae ; Sulcacis bidentulus ; Nederland ; verspreiding ; biologie ; herkenning ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 86
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    Vestiging van de boomkrekel Oecanthus pellucens in het rivierengebied (Orthoptera) (2013)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.39 (2013) p.35
    Details
    Publication Date: 2015-12-09
    Description: De boomkrekel is een slanke geelbruine krekel, die vooral opvalt door zijn melodieuze zang. Vroeger moest je naar Frankrijk om dit geluid te horen, maar tegenwoordig heerst ook in het rivierengebied bij Nijmegen een mediterrane sfeer. De boomkrekel is in 2004 voor het eerst langs de Waal gevonden en heeft zich daarna uitgebreid. In 2010 en 2011 heeft de Flora- en faunawerkgroep Gelderse Poort met vele vrijwilligers onderzoek gedaan naar de precieze verspreiding. In totaal werd de boomkrekel in 57 kilometerhokken gevonden en de verwachting is dat de soort zich de komende jaren verder zal uitbreiden.
    Keywords: Orthoptera ; Oecanthus pellucens ; Nederland ; verspreiding ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 87
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    De Nederlandse hongerwespen (Hymenoptera: Evanioidea: Gasteruptiidae) (2013)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.39 (2013) p.55
    Details
    Publication Date: 2015-12-09
    Description: Hongerwespen behoren tot de grote groep van de sluipwespen. Het zijn slanke wespjes die typisch met hangende pootjes vliegen, waarbij de verbrede achterschenen opvallen. Ze parasiteren bijen en mogelijk ook bepaalde angeldragende wespen en worden daarom vaak bij bijenhotels waargenomen. In het kader van dit artikel zijn de meldingen van Nederlandse hongerwespen kritisch beschouwd. In totaal zijn nu negen soorten uit ons land bekend, waarvan er hier maar liefst zes voor het eerst worden gemeld.
    Keywords: Hymenoptera ; Evanioidea ; Gasteruptiidae ; Nederland ; verspreiding ; herkenning ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 88
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    Marine fauna of hard substrata of the Cleaver bank and Dogger bank (2013)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.41 (2013) p.69
    Details
    Publication Date: 2015-12-09
    Description: As most of the sea bottom in the Dutch part of the North Sea consists of sand, marine fauna that live in association with hard substrates are rarely monitored. We report here on the results of a species inventory in June 2011 done by scuba-diving while focusing on a wreck on the Dogger Bank and on rocky bottoms on the Cleaver Bank. This resulted in various new records of species for the Dutch part of the North Sea. This result appeared for a large part linked to the added value of monitoring with scuba-divers. It is therefore concluded that scuba-divers should be used in addition to the more traditional monitoring methods in which dredges and grabs are used, if one aims at getting an accurate view of the biodiversity present in marine regions like the North Sea.
    Keywords: biodiversity ; hard substrata ; Netherlands ; marine ; scuba-diving ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 89
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    Benthic communities on hard substrates within the first Dutch offshore wind farm (OWEZ) (2013)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.41 (2013) p.59
    Details
    Publication Date: 2015-12-09
    Description: Five years after the commissioning of the offshore wind farm Egmond aan Zee, the monopiles and the rocks of the scour protection layers were covered by a wide variety of marine organisms. This paper describes the results of qualitative and quantitative assessments carried out in 2008 and 2011. The assessments were based on video footage, pictures and samples collected by divers at three different wind turbines. The ecological relevance of identified taxa is also discussed.
    Keywords: offshore wind farms ; Netherlands ; biodiversity ; benthic zone ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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  • 90
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    De gouden kegelbij Coelioxys aurolimbata teruggevonden in het rivierengebied (Hymenoptera: Apoidea: Megachilidae) (2013)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.40 (2013) p.39
    Details
    Publication Date: 2015-12-09
    Description: De gouden kegelbij Coelioxys aurolimbata is uit ons land recent alleen bekend uit de zuidelijke helft van Limburg. Vóór 1960 kwam deze parasiet van de lathyrusbij Chalicodoma ericetorum ook in het rivierengebied voor. In juli van dit jaar werd de gouden kegelbij gevangen in Duiven. Mogelijk is dit de voorbode van een herovering van het rivierengebied door deze bedreigde soort.
    Keywords: Hymenoptera ; Apoidea ; Megachilidae ; Nederland ; Coelioxys aurolimbata ; verspreiding ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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  • 91
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    The juwel anemone Corynactis viridis, a new order for the Netherlands (Cnidaria: Corallimorpharia) (2013)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.41 (2013) p.35
    Details
    Publication Date: 2015-12-09
    Description: During an expedition with scuba-divers to the Dutch part of the Brown Ridge in the central North Sea in June 2013, two colonies of the jewel anemone Corynactis viridis were found on the wreck Anna Graebe. With the jewel anemone both a new species and a new animal order, the Corallimorpharia, are added to the autochthonous fauna of the Netherlands. This species typically occurs in the Mediterranean and along the Atlantic coast from Portugal and the west British Isles up to Shetland. As other records of settled colonies of C. viridis in the North Sea were recently reported from Belgian, German and English waters, it is concluded that the jewel anemone, which used to be known as an occasional visitor, should now be considered autochthonous in the North Sea.
    Keywords: Cnidaria ; Corallimorpharia ; Netherlands ; Corynactis viridis ; distribution ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 92
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    De molkreeften Upogebia deltaura en U. stellata en geassocieerde soorten in de Noordzee (Decapoda: Upogebiidae) (2013)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.41 (2013) p.15
    Details
    Publication Date: 2015-12-09
    Description: In de bodem van de Noordzee leeft een bijzondere groep van kreeften. Zij brengen hun leven door in een ondergronds gangenstelsel: de molkreeften. Het zijn algemene bewoners van het Friese Front, de Oestergronden en de Klaverbank. In, op en bij deze kreeften leven verschillende andere diersoorten: parasitaire pissebedden, een mosdiertje en twee soorten tweekleppigen. Deze bijdrage gaat in op de ecologie van de molkreeften en hun symbionten.
    Keywords: Decapoda ; Upogebiidae ; Upogebia ; Nederland ; biology ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 93
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    Moss animals of the Dutch part of the North Sea and coastal waters of the Netherlands (Bryozoa) (2013)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.41 (2013) p.1
    Details
    Publication Date: 2015-12-09
    Description: Bryozoa or moss animals constitute a conspicuous and species-rich component of hardsubstrate benthic communities in marine and estuarine habitats. To gain insight into the biodiversity of these habitats, knowledge of bryozoan species is indispensable. Since the last comprehensive publication on Dutch species in 2004 much new information has become available. Particularly from the Dutch part of the Continental Flat of the North Sea, the largest natural area of the Netherlands, many new records have been collected. Other reasons to present an updated review are changes in nomenclature, the arrival of some exotic species and identification issues.
    Keywords: Bryozoa ; Netherlands ; checklist ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 94
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    Tephrochlaena oraria, een nieuwe afvalvlieg voor de Nederlandse fauna (Diptera: Heleomyzidae) (2013)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.40 (2013) p.35
    Details
    Publication Date: 2015-12-09
    Description: Heleomyzidae zijn kleine tot middelgrote vliegen. Ze krijgen niet veel aandacht, omdat de meeste soorten een nogal verborgen leven leiden en bovendien niet opvallend gekleurd of getekend zijn. De Nederlandse familienaam, afvalvliegen, is voor de meeste soorten niet echt passend, maar veel soorten van de subfamilie Heteromyzinae, waartoe Tephrochlaena oraria behoort, worden dan wel weer vaker rond afval aangetroffen. Tephrochlaena oraria is echter in meerdere opzichten een buitenbeentje. Met deze soort komt de lijst van Nederlandse Heleomyzidae op 49.
    Keywords: Diptera ; Heleomyzidae ; Tephrochlaena oraria ; Nederland ; verspreiding ; herkenning ; biologie ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 95
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    Komt de vermiljoenkever Cucujus cinnaberinus in azijnzuurvallen (Coleoptera: Cucujidae)? (2013)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.40 (2013) p.9
    Details
    Publication Date: 2015-12-09
    Description: Cucujus cinnaberinus is een recent voor Nederland ontdekte soort. De kever staat op de Habitatrichtlijn, wat onder meer betekent dat hij beschermd is en dat de populatie gemonitord dient te worden. Inventarisatie en monitoring gebeurt in het algemeen door het weghalen van schors van recent gestorven bomen. Hierdoor wordt het leefgebied van de kever echter flink aangetast. Wij voerden een klein onderzoek uit naar de mogelijkheden om C. cinnaberinus te vangen in azijnzuurvallen, zodat de habitat intact gelaten kan worden en de soort toch geïnventariseerd kan worden. Tijdens het voorjaar van 2013 werden vier vallen opgehangen op een locatie waar zich een populatie van deze soort bevindt. Er werden slechts twee individuen verzameld; de vangmethode lijkt dus niet bijzonder geschikt.
    Keywords: Coleoptera ; Cucujidae ; Cucujus cinnaberinus ; methode ; inventarisatie ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 96
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    Northward dispersal of the tanaid Zeuxo holdichi to the Netherlands (Crustacea: Tanaidae) (2013)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.39 (2013) p.95
    Details
    Publication Date: 2015-12-09
    Description: The tanaid Zeuxo holdichi, described in 1990 from Arcachon Bay in southwest France, has since then been recorded from west Portugal to northern Brittany and southwest England. The species is recorded here from the Netherlands, a further northward expansion of the range. It is hypothesised that Z. holdichi may be non-native to Europe.
    Keywords: Crustacea ; Tanaidae ; Zeuxo holdichi ; Netherlands ; distribution ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 97
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    Ecological relevance of shipwrecks in the North Sea (2013)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.41 (2013) p.49
    Details
    Publication Date: 2015-12-09
    Description: This paper reports on observations made during wreck dive expeditions in 2010-2012, in order to investigate the ecological relevance of shipwrecks on the Dutch Continental Shelf (dcs). Shipwrecks are biodiversity hotspots. The number of species recorded on shipwrecks is similar to the number of species found in soft bottoms of the entire dcs. The soft substrates, however, represent a vastly larger habitat on the dcs than the shipwrecks. Amongst many other taxa, juvenile and large Atlantic cod, linear skeleton shrimp, goldsinny wrasses and leopard spotted gobies were found in the shipwreck habitats. The presence of these important species and their absence from many other habitats, illustrate that shipwrecks function as key habitats, nurseries, and refugia that are rare or absent anywhere else in the Netherlands.
    Keywords: shipwrecks ; Netherlands ; biodiversity ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 98
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    De hottentottenvilla Villa hottentotta toch op de Nederlandse lijst (Diptera: Bombyliidae) (2013)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.40 (2013) p.23
    Details
    Publication Date: 2015-12-09
    Description: Wolzwevers zijn vliegen waarvan de larven parasitair leven bij andere insecten. Wolzwevers van het genus Villa veroorzaken vaak determinatieproblemen. Deze problemen lijken verleden tijd met recent gepubliceerde taxonomische inzichten. Eindelijk konden nu ook de Nederlandse exemplaren van dit genus op naam gebracht worden. Deze bleken te behoren tot vier soorten, waarvan er twee vermoedelijk reeds zijn verdwenen.
    Keywords: Diptera ; Bombyliidae ; Villa hottentotta ; Nederland ; verspreiding ; herkenning ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 99
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    De bijzondere levensloop van de sluipwesp Acrodactyla quadrisculpta op de schaduwstrekspin Tetragnatha montana (Hymenoptera: Ichneumonidae, Araneae: Tetragnathidae) (2013)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.39 (2013) p.1
    Details
    Publication Date: 2015-12-09
    Description: Sluipwespen van de groep van de Polysphinctini hebben een bijzondere levenswijze. Het vrouwtje van wesp legt een eitje op het achterlijf van een spin. Wanneer het eitje is uitgekomen brengt de larve haar hele leven op het achterlijf van de spin door. Ze maakt kleine wondjes in de huid en voedt zich met lichaamsvloeistof van de spin. Na verloop van tijd ontwikkelt de larve bulten op de rug, een teken dat ze bijna volgroeid is. Ze zuigt dan de spin leeg, de ‘grote slurp’ genaamd, en verpopt zich in het web. In dit artikel wordt de levenswijze van één van deze soorten, Acrodactyla quadrisculpta, voor het eerst beschreven en geïllustreerd.
    Keywords: Hymenoptera ; Ichneumonidae ; Araneae ; Tetragnathidae ; biologie ; Nederland ; Acrodactyla quadrisculpta ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 100
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    Galvormende bladwespen op wilg in Nederland (Hymenoptera: Tenthredinidae: Nematinae) (2013)
    In:  Nederlandse Faunistische Mededelingen (0169-2453) vol.39 (2013) p.15
    Details
    Publication Date: 2015-12-09
    Description: De bladwespgenera Phyllocolpa, Tubpontania, Pontania en Euura hebben gemeenschappelijk dat ze gallen vormen op wilg. Recentelijk is er veel vernieuwend taxonomisch werk verricht aan deze groepen. In dit artikel wordt de Nederlandse situatie samengevat. Uit oudere literatuur waren 18 soorten bekend en in het recent gepubliceerde gallenboek worden nog eens 11 soorten voor het eerst voor ons land vermeld. In dit artikel worden nog acht soorten aan de lijst toegevoegd en twee soorten worden van de lijst afgevoerd. In totaal zijn nu 35 soorten galvormende bladwespen van wilg uit Nederland bekend.
    Keywords: Hymenoptera ; Tenthredinidae ; Nematinae ; Nederland ; verspreiding ; herkenning ; 42.75
    Repository Name: National Museum of Natural History, Netherlands
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