ALBERT

Description: Abstract: Current information on the potential distribution and condition of peatland soils are of great importance. This applies notably for actions with respect to climate and environmental protection. The Ministry of infrastructure and agriculture in the federal state of Brandenburg (MIL) therefore initiated a project to provide a complete and updated map of peatland soils for the federal state of Brandenburg, Germany, for the year 2013. Extensive legacy data on both, areal extent of peatland soils as well as soil profile information where made digitally available in a homogeneous map and a consistent database. Approximately 7.725 sites were randomly selected from legacy soil data and currently reinvestigated to draw inference on the current condition of peatland soils. Statistically derived peatland subsidence rates at grassland sites of 0.50 cm/yr and 0.57 cm/yr at arable sites fit well with published values in comparable regions of central Europe. Our results prove the great dynamics of soil development on agriculturally used peatlands. Concerning Brandenburg, the area of peatland soils decreased from 270.000 ha in the early 20th century (Prussian geological map) to actually 163.000 ha.

Description: Zusammenfassung: Aktuelle Informationen zur Verbreitung und zum Zustand der Moorböden sind vor dem Hintergrund der geplanten Einführung von Agrarumwelt- und Klimamaßnahmen in der Landwirtschaft von besonderer Bedeutung. Das Ministerium für Infrastruktur und Landwirtschaft des Landes Brandenburg (MIL) hat hierzu das Projekt „Schaffung einer Datengrundlage für die Ableitung von Agrarumwelt- und Klimamaßnahmen auf Moorstandorten in Brandenburg“ initiiert. Mit dem Ziel der Bereitstellung einer auf das Jahr 2013 bezogenen Moorkarte wurden umfangreiche, bis dato nicht genutzte Datenbestände zur Verbreitung von Moorböden in Brandenburg zu einer überschneidungsfreien Karte und umfassenden Datenbank moorbodenkundlicher Bodenprofile verarbeitet. Um den aktuellen Zustand der Moorböden zu erfassen, wurden flächenrepräsentativ und zufällig an 7.725 Standorten mit ausreichender Datenbasis erneut bodenkundliche Erhebungen durchgeführt und statistisch ausgewertet. Im Ergebnis konnten Mächtigkeitsverlustraten für landwirtschaftlich genutzte Moorstandorte in Brandenburg abgeleitet werden. Für flachgründige Niedermoorstandorte unter Grünland liegen sie bei 0,50 cm/a, vergleichbare ackerbaulich genutzte Standorte liegen mit 0,57 cm/a darüber. Dies deckt sich gut mit publizierten Werten an vergleichbaren Standorten in Zentraleuropa. Die Fläche der Moorböden in Brandenburg hat sich von Anfang des 20. Jahrhunderts von 270.000 ha, ausgewiesen auf Basis der Preußisch geologisch-agronomische Karte (PGK), auf heute noch 163.000 ha reduziert.

Description: DFG, SUB Göttingen, DGMT

Description: research

Description: Inhaltsverzeichnis : EHLERS, J. & MENSCHING, H.: Küstenversatz und Prielverlagerungen an der Nordseeküste. S. 9-22 ; FRÄNZLE, O.: Periglaziäre Formung der Altmoränengebiete Schleswig-Holsteins. S. 23-35 ; HEMPEL, L.: Rezente und fossile Mesoformen der Abtragung und Aufschüttung in Ausräumen von Schichtkammlandschaften im Teutoburger Wald. S. 37-47 ; LEHMEIER, F.: Zum Formenschatz der Schichtkammlandschaft im Niedersächsischen Bergland. S. 49-61 ; GARLEFF, K., BRUNOTTE, E. & STINGL, H.: Fußflächen im zentralen Teil der Hessischen Senke. S. 63-76 ; MÖLLER, K.: Das Eschweger Becken und seine Randbereiche — Ergebnisse geomorphographischer und hydrochemischer Analysen. S. 77-92 ; GLATTHAAR, D.: Vertikalbewegungen und ihre Bedeutung für die Formenentwicklung im Westerwald. S. 93-106 ; MÜLLER, M.J.: Periglaziärfluviale, solifluidale und abluale Formung im westlichen Hunsrück und am Ostrand der Trier-Bitburger Mulde. S. 107-118 ; BARSCH, D. & MÄUSBACHER, R.: Zur fluvialen Dynamik beim Aufbau des Neckarschwemmfächers. S. 119-128 ; LESER, H.: Schichtstufen und Talrandstufen in Südwestdeutschland. S. 129-147 ; FARRENKOPF, D.: Relief und Wasserhaushalt im Eyachtal, Nordschwarzwald. S. 149-154 ; LESER, H. & METZ, B.: Vergletscherungen im Hochschwarzwald. S. 155-175 ; HABBE, K.A.: Was kann eine geomorphologische Vollkartierung für die Stratigraphie des Quartärs leisten? S. 177-196 ; RATHJENS, C.: Jungglaziale Formung und spätglazialer Eisabbau im Chiemgau. S. 197-205 ; FISCHER, K.: Die würmzeitliche und stadiale Vergletscherung der Berchtesgadener Alpen. S. 207-225 ;

Description: research

Description: DFG, SUB Göttingen

Description: Zur Vereinfachung wird die Vielfalt der Karstformenbezeichnungen bereinigt. Erdfall wird als Form, die in nicht verkarstungsfähigen Serien liegt, aber auf Tiefensubrosion zurückgeht, der Doline, einer Form, die in verkarstungsfähigem Material liegt, gegenübergestellt. Als Grundlage der Arbeit wurde eine detaillierte Kartierung der Auslaugungsformen durchgeführt. Hinsichtlich rezenter Subrosion erwies es sich als notwendig, die in Oberflächenwässern und wasserwirtschaftlich erfaßten Wässern gelösten Bestandteile von Chlorid, Sulfat und Karbonat zu ermitteln. Die Auswertung der gewonnenen Daten zeigt, daß ein Zusammenhang mit Gebieten besteht, die durch aktuelle Erdfälle und Dolineneinbrüche gekennzeichnet sind. Als Voraussetzung zur Reliefgenese gilt, daß das Gebiet des Unterwerra-Sattels entscheidend durch die saxonische Gebirgsbildung an der Wende Jura/Kreide und die nachfolgende klimageomorphologische Entwicklung geprägt ist. Anhand der geomorphographischen Analyse wird der Einfluß der Salz-, aber auch der Sulfatauslaugung auf die Landschaftsgenese belegt. Die Auslaugung des Salzes (Nal), dessen Mächtigkeit im Untersuchungsgebiet mit mindestens 120 m angenommen wird, und der unterlagernden ca. 130 m nächtigen Zechsteingipse (A 1 - A 3) zerrüttet die überlagernden triassischen Schichten weiter. Darüber hinaus wirkt die Subrosion von mehr als 30 m Rötgipsen und 50 m Gipsen des Mittleren Muschelkalkes im Hangenden des Zechsteins reliefformend. Die ermittelten Ergebnisse - rezente und subrezente Formen, Lösungswerte – werden zunächst in kleineren Gebietseinheiten analysiert. Die Ergebnisse der Nasseranalysen bestätigen das geomorphographische Ergebnis, so daß in Anlehnung an die Gipshorizonte von Stockwerkssubrosion gesprochen werden kann. Entscheidend geprägt ist die heutige Situation jedoch durch vorangegangene Zechsteinsalzauslaugung im tieferen Untergrund. Diese hat in den Hangendserien die Wasserwegsamkeit verstärkt, so daß die nachfolgende Sulfatsubrosion den Kleinformenschatz vor der Schichtstufe des Mittleren Buntsandsteins steuern konnte. Aufgrund ihrer für Auslaugungsgebiete typischen Ausprägung wird die Lage der Schichtstufe in weiten Teilen des Untersuchungsgebietes an das in Auslaugung befindliche Salz geknüpft. Das Auftreten von Subrosionsformen vor der Landstufe des Kaufunger Waldes, den östlichen Meißnerhängen, dem Anstieg des Schlierbachswaldes sowie vor dem Anstieg des Buntsandsteins zwischen Heldra, Frieda und Bad Sooden-Allendorf untermauert diese Interpretation. In der südlichen und südöstlichen Umrahmung des Untersuchungsgebietes wird der Salzhang aufgrund geomorphographischer Kriterien unter dem Steilanstieg des Unteren Muschelkalkes ausgewiesen. Aufgrund dieser Befunde wird die primäre Salzverbreitung als über den Unterwerra-Sattel reichend angenommen, womit sich, abgesehen von den Einflüssen der saxonischen Tektonik, alle Reliefentwicklungsprozesse allein durch Auslaugung und folgende geomorphologische Überprägung erklären lassen. Darüber hinaus ist dieses Gebiet in Nordhessen nicht nur durch eine über alle Schichten hinweggreifende Rumpfflächenbildung gekennzeichnet, sondern die Resistenzunterschiede wurden - unabhängig vom Klima - beständig herausgearbeitet. Aus diesen Ergebnissen wurde ein übergeordnetes Modell zur Reliefentwicklung erstellt. Danach existieren im Untersuchungsgebiet fünf Reliefgenerationen, wobei die postsaxonische Reliefentwicklung mit zerstörtem, die Auslaugung begünstigendem Hangendverband nach der Landhebung bzw. dem Einbruch der das Gebiet begrenzenden Grabenstrukturen, die bis ins Alttertiär reicht, nicht erfaßt werden konnte. [...]

Description: research

Description: DFG, SUB Göttingen

Description: In der vorliegenden Arbeit wurden Ergebnisse hydrologischer und stratigraphischer Studien zur Entwicklungsgeschichte von Brandenburger Kesselmooren vorgestellt. Für die Erfassung der aktuellen und historischen biotischen und abiotischen Standortfaktoren wurden verschiedene Methoden angewandt: floristische und vegetationskundliche Untersuchungen sowie hydrologische, hydrochemische, geochemische, geophysikalische und sedimentologische Untersuchungen und Makrorest-‚ Mikrorest- und Pollenanalyse. Der zeitlichen Einordnung der entwicklungsgeschichtlichen Prozesse dienten Radiocarbondatierungen und die pollenanalytischen Untersuchungen. Ziel der Arbeit war es, Entwicklungsstadien auszuscheiden, die von den untersuchten Mooren seit ihrer Entstehung durchlaufen wurden. Aufgrund der stratigraphischen Untersuchungen wurden Aussagen zur Beckengenese und zu den einzelnen See- und Moorentwicklungsphasen getroffen, zum Verlandungsvorgang, zu Moorbildungsbedingungen und Sukzessionsstadien. Den Entwicklungsstadien konnten über geochemische und -physikalische Untersuchungen abiotische Standortfaktoren zugeordnet werden. Die aktuellen Standortveränderungen wurden erfaßt und die vorgenommenen Erhaltungs- und Wiedervernässungsmaßnahmen dokumentiert und bewertet.

Description: research

Description: DFG, SUB Göttingen

Description: Dieser Band enthält 63 Artikel zu Themengebieten der Physik der festen Erde, zu magnetischen und elektrischen Feldern der Erde, zu der Physik der Atmophäre und der angewandten Geophysik veröffentlicht durch die Deutsche Geophysikalische Gesellschaft in dem Jahr 1934.

Description: 〈html〉 〈body〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0004.pdf"〉Titelseite〈/a〉〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0005.pdf"〉Autorenverzeichnis〈/a〉〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0006.pdf"〉Sachverzeichnis〈/a〉〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0007.pdf"〉Karl Mack †〈/a〉〈br〉(Hiller, W.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0008.pdf"〉Die südalbanischen Erdbeben 1930/31〈/a〉〈br〉(Nowack, E.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0009.pdf"〉Seismische Untersuchungen des Geophysikalischen Instituts in Göttingen〈/a〉〈br〉(Gräfe, H., v. zur Mühlen, W., Müller, H. K.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0017.pdf"〉Horizontalsicht bei örtlich veränderlicher Trübung und Beleuchtung〈/a〉〈br〉(Steinhäusser, H.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0018.pdf"〉Referate und Mitteilungen〈/a〉〈br〉(Haase, H., Köhler, R., Berroth, A.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0019.pdf"〉Beitrag zur Berechnung von Minimum-Stabpendeln〈/a〉〈br〉(Graf, A.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0020.pdf"〉Zur Theorie elastischer Pendel mit besonderer Berücksichtigung des Holweck-Lejayschen Stabpendels〈/a〉〈br〉(Graf, A.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0021.pdf"〉Eine neue Methode für sehr präzise magnetische Messungen〈/a〉〈br〉(Koulomzine, T., Bondaletoff, N.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0022.pdf"〉Zur Frage der mit dem temperaturkompensierten Magnetsystem erreichbaren Meßgenauigkeit〈/a〉〈br〉(Kohl, E.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0023.pdf"〉Die Höhenverteilung der Erd-, Luft- und Höhenstrahlung〈/a〉〈br〉(Suckstorff, G. A.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0024.pdf"〉Erdstrahlungsmessungen in Bad Nauheim nach der Gammastrahlenmethode〈/a〉〈br〉(Masuch, V.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0025.pdf"〉Referate〈/a〉〈br〉(Jung, H.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0026.pdf"〉Abschnitt〈/a〉〈br〉(Angenheister, G., Kohlschütter, E.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0027.pdf"〉Hergesell geb. 29. Mai 1859〈/a〉〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0028.pdf"〉Hecker geb. 21. Mai 1864〈/a〉〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0029.pdf"〉Sprengungen zur Forschungszwecken mit Unterstützung der Notgemeinschaft der Deutschen〈/a〉〈br〉(Duckert, P.)〈/a〉〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0037.pdf"〉Beiträge zu den Luftschallmessungen〈/a〉〈br〉(Meißer, O., Martin, H.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0039.pdf"〉Seismische Untersuchungen des Geophysikalischen Instituts in Göttingen〈/a〉〈br〉(Regula, H.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0042.pdf"〉Berechnung der Laufzeitkurven des anormalen Schalles für windstille Atmosphäre und Vergleich mit der Laufzeitkurve der Oldebroek-Sprengung vom 15. Dezember 1932〈/a〉〈br〉(Jung, H.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0043.pdf"〉Ergebisse der Registrierungen von Schallwellen an kreisförmig um den Sprengherd angeordneten Stationen〈/a〉〈br〉(Duckert, P.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0044.pdf"〉Beobachtungsergebnisse über den Einfluß der "akustischen Umkehrschicht" auf die Schallausbreitung〈/a〉〈br〉(Sandmann, B.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0045.pdf"〉Zur Frage der anomalen Schallausbreitung〈/a〉〈br〉(Kölzer, J.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0046.pdf"〉Schalluntersuchungen im Polargebiet〈/a〉〈br〉(Wölcken, K.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0049.pdf"〉Betrachtungen über ebene Pendel〈/a〉〈br〉(Hahnkamm, E.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0051.pdf"〉Außenraum und Innenraum (Schlichtung des Streites um die Schwerkraftreduktion)〈/a〉〈br〉(Schwinner, R.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0052.pdf"〉Bemerkungen zu den Geoiden von Ackerl und Hirvonen〈/a〉〈br〉(Ledersteger, K.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0053.pdf"〉Auto-Radio als Hilfsmittel geologischer Kartierung〈/a〉〈br〉(Cloos, E.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0054.pdf"〉Zur photographischen Registrierung von Stationsseismometern〈/a〉〈br〉(Meißer, O.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0056.pdf"〉Ein Horizontalseismometer für die Aufzeichnung von starken Orts- und Nahbeben〈/a〉〈br〉(Critikos, N. A.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0059.pdf"〉Die Bedeutung der Unstetigkeiten im Verlauf der Schallgeschwindigkeit mit der Höhe für die normale und anomale〈/a〉〈br〉(Sandmann, B.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0060.pdf"〉Referate und Mitteilungen〈/a〉〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0061.pdf"〉Die Relativität der Undulationen〈/a〉〈br〉(Hopfner, F.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0062.pdf"〉Ein detonierendes Meteor über dem Weserbergland am 2. Januar 1934〈/a〉〈br〉(Hartmann, W.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0063.pdf"〉Der Meteorfall bei Stadt Rehburg am 2. Januar 1934〈/a〉〈br〉(Trommsdorff, W.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0064.pdf"〉Vergleich zwischen der Intensität der kosmischen Ultrastrahlung über Grönland und über Deutschland〈/a〉〈br〉(Wölcken, K.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0065.pdf"〉Das Grundeis〈/a〉〈br〉(Jakuschoff, P.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0066.pdf"〉Le problème des microséismes et le déferlement des vagues〈/a〉〈br〉(Gherzi, E.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0067.pdf"〉Note on the Hayford-Bowie tables for calculation 〈i〉g〈/i〉〈/a〉〈br〉(Bullard, E. C.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0068.pdf"〉Kann die Laplacesche Differentialgleichung für das Schwerkraftpotential auch innerhalb der Erdkruste als erfüllt angesehen werden?〈/a〉〈br〉(Grabowski, L.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0069.pdf"〉Vorträge, gehalten auf der XI. Tagung der Deutschen Geophysikalischen Gesellschaft, am 13. bis 15. September 1934 in Pyrmont〈/a〉〈br〉(Jung, K.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0072.pdf"〉Der geophysikalische Nachweis des Zechsteindolomits〈/a〉〈br〉(Müller, M.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0073.pdf"〉Berichtigung〈/a〉〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0074.pdf"〉Vorträge, gehalten auf der XI. Tagung der Deutschen Geophysikalischen Gesellschaft, am 13. bis 15. September 1934 in Pyrmont〈/a〉〈br〉(von Seidlitz, W., Sieberg, A., Linke, F., Gerlach, W.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0079.pdf"〉Zur Frage der Geländekorrektion bei Drehwaagemessungen〈/a〉〈br〉(Tuchel, G.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0080.pdf"〉Emanation in Boden- und Freiluft〈/a〉〈br〉(Israël, H.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0081.pdf"〉Die Energie der Heliokathodenstrahlen in ihrer Beziehung zur fortschreitenden Bewegung der Elektronen in den Polarlichtstrahlen〈/a〉〈br〉(Rudolph, H.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0082.pdf"〉Weitere Untersuchungen mit dem Sanford-Elektrometer〈/a〉〈br〉(Stoppel, R.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0083.pdf"〉Das Strömungssystem der Luft über Mogadischu〈/a〉〈br〉(Bossolasco, M.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0084.pdf"〉Messungen mit transportablen statischen Schweremessern〈/a〉〈br〉(Schleusener, A.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0086.pdf"〉Über den Energietransport bei der Sprengseismik〈/a〉〈br〉(v. Schmidt, O.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0087.pdf"〉Formen der Bodenschwingung bei sinusförmiger Anregung〈/a〉〈br〉(Köhler, R.)〈/li〉 〈li〉〈a href=" https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0088.pdf"〉Die Ausbreitungsgeschwindigkeit sinusförmiger elastischer Wellen im Boden〈/a〉〈br〉(Ramspeck, A.)〈/li〉 〈li〉〈a href=" https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0089.pdf"〉Referate und Mitteilungen〈/a〉〈br〉(Haase, H.)〈/li〉 〈li〉〈a href=" https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0090.pdf"〉Bericht über die elfte Tagung der Deutschen Geophysikalischen Gesellschaft vom 13. bis 15. September 1934 in Bad Pyrmont〈/a〉〈br〉(Jung, K.)〈/li〉 〈li〉〈a href=" https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0091.pdf"〉Berichtigung〈/a〉〈/li〉 〈li〉〈a href=" https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0092.pdf"〉Geophysikalische Berichte〈/a〉〈/li〉 〈li〉〈a href=" https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0093.pdf.pdf"〉Register der Geophysikalischen Berichte〈/a〉〈/li〉 〈li〉〈a href=" https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0010/LOG_0094.pdf"〉Mitgliederverzeichnis der Deutschen Geophysikalischen Gesellschaft nach dem Stande vom 1. Dezember 1934〈/a〉〈/li〉 〈/body〉 〈/html〉

Description: research

Description: DGG, DFG, SUB Göttingen

Description: Deutschlands Erdbebentätigkeit pflegt unterschätzt zu werden, weil sie gewöhnlich so harmlos erscheint. Zwar bringt der Jahresverlauf nur wenige Beben, abgesehen von gelegentlichen Schwärmen mit vielen hunderten von Einzelstößen, wie sie besonders dem Vogtland eigentümlich sind. Zudem handelt es sich dabei vorwiegend um schadlose Erderschütterungen, die kaum Beobachtung finden. Aber der Fachmann kennt daneben auch bis in die neueste Zeit hinein Erdbeben mit erheblichen Schäden und selbst Zerstörungen, die für längere Zeit das öffentliche Leben völlig beherrscht haben; mitunter wurde fast Großbebencharakter erreicht.

Description: research

Description: DFG, SUB Göttingen

Description: Die nachstehenden neueren Untersuchungen auf verschiedenen Gebieten geophysikalischer Forschung, die von Mitgliedern der Reichsanstalt für Erdbebenforschung in Jena durchgeführt sind, wurden erstmalig in der Festschrift zum 70. Geburtstage des früheren Direktors der Reichsanstalt, Herrn Geheimrat Professor Dr. Oskar Hecker (Beitrage zur Angewandten Geophysik, Band 4, Heft 3, Leipzig 1934) veröffentlicht. Sämtliche Arbeiten, ausgenommen diejenigen von Krumbach, gehören zu den von der Notgemeinschaft der Deutschen Wissenschaft unterstützten geophysikalischen Forschungen. A. Sieberg

Description: research

Description: DFG, SUB Göttingen

Description: Abstract: Peatlands are intensively exchanging greenhouse gases with the free atmosphere. Natural peatlands, mires, sequester carbon dioxide as carbon in the peat and emit methane. Peatlands under agriculture or forest are mostly drained and emit carbon dioxide due to peat mineralization and nitrous oxide due to fertilization and nitrogen mineralization. In order to characterize the actual situation and to evaluate measures for the reduction of greenhouse gas emissions measured values on gas exchange are needed. Within two national projects direct measurements of the greenhouse gas exchange have been conducted on a wide range of sites, covering different peatland types, land use forms and hydrological situations and using a standardized methodology. Between 2007 and 2012 22 sites have been studied in Lower Saxony over at least two years using the closed cover method. An overview on sites and results is given. Moreover, approaches to estimate the greenhouse gas emissions due to peat excavation and horticultural peat use are presented. Own emission factors and data from literature are used to estimate the contribution of peatlands and peat use to the greenhouse gas emissions of Lower Saxony. Finally measures for the reduction of greenhouse gas emissions are discussed and estimates on reduction costs are given from examples.

Description: Zusammenfassung: Moore stehen in einem intensiven Gasaustausch mit der Atmosphäre. Natürliche Moore haben über Jahrtausende Kohlendioxid aufgenommen und den Kohlenstoff als Torf gespeichert. Dabei haben sie Methan abgegeben. Entwässerte und genutzte Moore setzen den Kohlenstoff als Kohlendioxid wieder frei und emittieren zudem klimarelevantes Lachgas als Ergebnis der Stickstoffdüngung und der Torfmineralisation. Zur Charakterisierung der Ist-Situation und zur Beurteilung von Maßnahmen ist es erforderlich, belastbare Daten über die Treibhausgasemissionen der Moore zu haben. Im Rahmen von zwei bundesweit angelegten Verbundvorhaben wurden an einer Vielzahl von Standorten unterschiedlichen Moortyps, unterschiedlicher Nutzung und unterschiedlicher Klima- und Wasserregime mit einer abgestimmten Methodik die Flüsse der wesentlichen Treibhausgase direkt gemessen. Im Rahmen dieser Verbundvorhaben wurden in Niedersachsen zwischen 2007 und 2012 an 22 Standorten mindestens zweijährige Messungen mit der Haubentechnik vorgenommen. Dieser Beitrag gibt einen Überblick über untersuchte Standorte und Messergebnisse. Darüber hinaus werden Ansätze zur Ermittlung der Treibhausgasemissionen aus der industriellen Torfgewinnung dargestellt. Unter Verwendung eigener Ergebnisse und von Literaturdaten wird eine Abschätzung der Treibhausgasemissionen aus Moor und Torfgewinnung für das Land Niedersachsen vorgenommen. Abschließend geht der Beitrag auf Maßnahmen zur Verminderung der Treibhausgasemissionen aus Mooren sowie beispielhaft auf Emissionsminderungskosten ein.

Description: DFG, SUB Göttingen, DGMT

Description: research

Description: STÄBLEIN, G.: Regionale Geomorphologie ; KERTESZ, A.: Geomorphologische Kartierung in der Bundesrepublik Deutschland und in Ungarn. Ein Vergleich der Methodik ; BOLLMANN, I.: Geomorphologische Daten und kartographische Darstellung ; PACHUR, H.-J. & RÖPER, H.-P.: Geolimnologische Befunde des Berliner Raumes ; REMMELE, G.: Holozäne Morphodynamik an Schichtstufenhängen — Untersuchungen in Nordwest-Irland ; MÜLLER, MJ. & STRASSER, R.: Holozäne Geomorphodynamik und Landschaftsentwicklung am Ostrand der Trier-Luxemburger Mulde ; KLEBER, A.: Zur jungtertiären Reliefentwicklung im Vorland der südlichen Frankenalb ; HAMANN, C.: Windwurf als Ursache der Bodenbuckelung am Südrand des Tennengebirges, ein Beitrag zur Genese der Buckelwiesen ; ZÖLLER, L.: Neotektonik am Hunsrückrand ; SEPPÄLÄ, M.: Glazialhydrologie des Inlandeises, eine geomorphologische Interpretation der Verhältnisse in Finnland ; JÄKEL, D.: Untersuchungen und Analysen zur Entstehung der Hamada ; GARLEFF, K. & STINGL, H.: Neue Befunde zur jungquartären Vergletscherung in Cuyo und Patagonien ; STINGL, H. & GARLBFF, K.: Tertiäre und pleistozäne Reliefentwicklung an der interozeanischen Wasserscheide in Südpatagonien (Gebiet von Rio Turbio, Argentinien) ; SCHMIDT, K.H.: Nachweis junger Krustenbewegungen auf dem Colorado Plateau, USA ; KUHLE, M.: Zur Geomorphologie Tibets, Bortensander als Kennformen semiarider Vorlandvergletscherung . ; STÄBLEIN, G.: Deutscher Arbeitskreis für Geomorphologie ;

Description: research

Description: DFG, SUB Göttingen, FU Berlin

Description: Abstract: In addition to the widespread use of peatlands for agricultural purposes, which is also common in other German states, the raised bogs in Lower Saxony are still also used up to the present day for housing, as well as for industrial peat extraction. The Peatland Conservation Programme in Lower Saxony launched in 1981 therefore only covered raised bogs to disentangle the different uses, and to systematise the nature protection activities in raised bogs. The priority areas for the extraction of peat defined in the Federal State Regional Planning Programme are to be rescinded. The new State Development Programme being formulated will not only include the nature conservation of peatlands, but also for the first time, deal with the climate protection afforded by these very important storage areas for carbon. An important aspect in this regard is the incorporation of fens, and the discharge from peatlands into underlying water bodies. The database and the conclusions which contribute to the implementation of climate protection in peatland conservation programmes, will be discussed and compared with the peatland conservation previously implemented pursuant to the Peatland Conservation Programme in Lower Saxony. An overview describes various approaches for peatland and climate protection implemented by private initiatives, nature conservation societies, EU-Life-Projects, contractual nature protection, publicly owned businesses and authorities in Lower Saxony, research projects on alternative uses, and climate certificate trading. These varied instruments are compared to highlight their relative areal effectiveness, and relevance, followed by an estimate of the potential for future peatland and climate protection in Lower Saxony.

Description: Zusammenfassung: Neben der auch in anderen Bundesländern weit verbreiteten landwirtschaftlichen Nutzung von Mooren werden die niedersächsischen Hochmoore bis heute auch als Siedlungsraum und zur industriellen Torfgewinnung genutzt. Daher umfasste das niedersächsische Moorschutzprogramm von 1981 nur die Hochmoore, um diese verschiedenen Nutzungen zu entflechten und den Naturschutz in Hochmooren zu systematisieren. Die bisher im Landesraumordnungsprogramm ausgewiesenen Vorranggebiete für die Rohstoffgewinnung von Torf sollen gestrichen werden. In ein neu aufzustellendes Landesentwicklungsprogramm soll neben dem Naturschutz von Mooren erstmalig auch der Klimaschutz dieser wichtigen Kohlenstoffspeicher eingehen. Von besonderer Bedeutung sind hierbei die Einbeziehung der Niedermoore und der Stoffaustrag aus Mooren in unterliegende Gewässer. Die Datengrundlagen und Schlussfolgerungen, die zur Implementierung des Klimaschutzes in den Moorschutz beitragen, werden diskutiert und mit dem bisher umgesetzten Moorschutz nach dem niedersächsischen Moorschutzprogramm verglichen. Ein Überblick beschreibt verschiedene Ansätze zum Moor- und Klimaschutz von Privatinitiativen, von Naturschutzverbänden, mit EU-Life-Projekten, im Vertragsnaturschutz, von niedersächsischen Landesbetrieben und Behörden, von Forschungsprojekten zu alternativen Nutzungen und beim Handel mit Klima-Zertifikaten. Diese unterschiedlichen Instrumente werden in ihrer Flächenwirksamkeit und Relevanz in Beziehung gesetzt und das Potenzial für den künftigen Moor- und Klimaschutz in Niedersachsen abgeschätzt.

Description: DFG, SUB Göttingen, DGMT

Description: research

Description: Am Beispiel des "Leegmoores" im Timpemoor - einem ehemaligen "Heidemoor" - wurde auf Grund von boden- und moorkundlichen Untersuchungen sowie von landeskundlich-historischen Recherchen die Entwicklung der Heidemoore überprüft. Dazu wurden erstmalig die flächenhaften Verluste an Moorsubstanz durch - wiederholte Moorbrandkultur, - Entnahme von Heidesoden (Abplaggen) und - Winderosion qualitativ und quantitativ erfaßt, dazu die Moorsackung errechnet. Aus den vorhandenen moorkundlichen Fakten konnte das natürliche Moorrelief des Timpemoores rekonstruiert werden. Die Autoren weisen nach, daß die von JONAS (1934, 1935) beschriebenen Heidemoore "durch den Menschen beeinflußte Moore" darstellen. Das untersuchte Timpemoor hat sich danach im Verlauf mehrerer Jahrhunderte aus einem natürlichen gewölbten Hochmoor gebildet.

Description: On the basis of pedological, peatland and historical investigations the origin of raised bogs with heather vegetation ("Heidemoore")was examined at the example "Leegmoor", a part of the "Timpemoor". In addition to that for the first time the loss of peat substance by - burnt-over peatland cultivation, - cutaway heather sods, - erosion by wind and - bog subsidence was calculated. With the available peatland facts it was possible to reconstruct the natural bog relief. The authors are able to demonstrate that the "Heidemoore" described by JONAS (1934, 1935) are bogs influenced by man. During the last centuries the Timpemoor developed from a natural raised bog (with convex centre) to a raised bog with heather vegetation.

Description: research

Description: DFG, SUB Göttingen

Description: Vergleichende Darstellung und Analyse der Arbeitsvorgänge in den Agrarlandschaften der Erde. Dieser Aufgabe unterzieht sich in einem ersten Schritt die vorliegende Studie. Sie strebt an, mit der Darstellung und Analyse des jährlichen Arbeitsvorganges die bisher wenig berücksichtigte dynamische Seite der Agrarlandschaft – ihre Rhythmik nämlich – in exakter Weise erfassen zu können. Im Vordergrund steht zunächst weniger die regionale als vielmehr die sachliche Erörterung, auf der Beispielsgrundlage jedoch einer regionalen Kontrastierung innerhalb Deutschlands bzw. aus naheliegenden Gründen der Bundesrepublik Deutschland. Späteren großräumigen Untersuchungen erst kann es vorbehalten sein, von der hier geschaffenen Plattform aus auf eine speziell regionale Betrachtungsweise überzugehen.

Description: research

Description: DFG, SUB Göttingen

Description: An der Hand von Erdbeben, die im Boden Deutschlands entstanden sind, sollen folgende Fragen untersucht werden: 1) Die Wirkungsweise der einzelnen Bebenherde, von denen anzunehmen ist, dass sie verschiedenartige Charaktereigenschaften haben. Hierfür ist es notwendig, festzustellen einmal Lage und geometrisches Bild des Herdes als geologische Störungsstelle, andererseits den das Erdbeben auslösenden Bewegungsvorgang in der Herdstörung. 2) Die Abhängigkeit der scheinbaren Bebenstarken innerhalb des Schüttergebietes von Bodenbeschaffenheit und Tektonik.

Description: research

Description: DFG, SUB Göttingen

Description: Dieser Band enthält 77 Beiträge zu Themengebieten der Physik der festen Erde, des magnetischen und elektrischen Felds der Erde, der Physik der Atmosphäre sowie der Angewandten Geophysik, veröffentlicht durch die Deutsche Geophysikalische Gesellschaft in den Jahren 1930.

Description: 〈html〉 〈body〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0004.pdf"〉Titelseite〈/a〉〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0005.pdf"〉Ein neuer Vierpendelapparat für relative Schweremessungen〈/a〉〈br〉(Meisser, O.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0007.pdf"〉Geophysikalische Messungen unter Tage〈/a〉〈br〉(Meisser, O., Wolf, F.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0008.pdf"〉Die ersten Dickenmessungen des grönländischen Inlandeises〈/a〉〈br〉(Sorge, E.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0010.pdf"〉Die seismische Bodenunruhe in Hamburg und ihr Zusammenhang mit der Brandung〈/a〉〈br〉(Mendel, H.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0012.pdf"〉Die sonnenbelichteten Nordlichtstrahlen und die Konstitution der höheren Atmosphärenschichten〈/a〉〈br〉(Vegard, L.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0013.pdf"〉Nochmals: Zur Frage der Laufzeitkurven〈/a〉〈br〉(Gutenberg, B.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0014.pdf"〉Erwiderung zur vorstehenden Arbeit von Herrn Prof. Gutenberg〈/a〉〈br〉(Krumbach, G.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0015.pdf"〉Bemerkungen zu der vorstehenden Erwiderung〈/a〉〈br〉(Gutenberg, B.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0016.pdf"〉Einfluß des Mondes auf die erdmagnetischen Elemente in Samoa〈/a〉〈br〉(Fanselau, G.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0017.pdf"〉Ein Diagramm zur Bestimmung der Differenz der Schwerestörung 〈i〉Δg〈/i〉 in zwei Beobachtungspunkten〈/a〉〈br〉(Oserezky, W.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0018.pdf"〉Zur Ermittlung ausgedehnter Schichten verschiedener Leitfähigkeit〈/a〉〈br〉(Koenigsberger, J.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0019.pdf"〉Über tägliche erdmagnetische Variationen in zwei Alpentälern〈/a〉〈br〉(Koenigsberger, J.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0020.pdf"〉Die Wirkung der obersten Erdschicht auf die Anfangsbewegung einer Erdbebenwelle〈/a〉〈br〉(Hasegawa, M.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0021.pdf"〉Über die Elastizität von Gesteinen〈/a〉〈br〉(Breyer, H.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0023.pdf"〉Über den Horizontalabstand von Pendelstationen〈/a〉〈br〉(Schwinner, R.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0024.pdf"〉Die Belowsche Methode zur Bestimmung der Wirkung gegebener Massen auf Krümmungsgröße und Gradient, ihre Verallgemeinerung für beliebige Massenformen und ihre Anwendung auf "zweidimensionale" Massenanordnungen〈/a〉〈br〉(Jung, K.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0028.pdf"〉Harmonische Schwingungen des Untergrundes〈/a〉〈br〉(Köhler, R.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0029.pdf"〉Mitteilungen〈/a〉〈br〉(Fleming, I. A., Linke, F.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0030.pdf"〉Über die Ursache der erdmagnetischen Störung im Gebiet der Freien Stadt Danzig〈/a〉〈br〉(Haalck, H.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0031.pdf"〉Die kontinentalen Verschiebungen von Amerika und Madagaskar〈/a〉〈br〉(Livländer, R.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0032.pdf"〉Magnetische Vermessung einiger tertiärer Eruptivgänge und -stöcke im sächsischen Elbsandsteingebirge〈/a〉〈br〉(Schulze, E.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0033.pdf"〉Über die Existenz einer mondentägigen Variation in den Erdströmen〈/a〉〈br〉(Egedal, J.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0034.pdf"〉Zum Trübungsfaktor〈/a〉〈br〉(Feussner, K., Friedrichs, H.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0035.pdf"〉Temperature changes between Torsion balance readings in the State of Texas〈/a〉〈br〉(Harris, S.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0036.pdf"〉Über isostatische Schwereanomalien und deren Beziehung zu den totalen Anomalien〈/a〉〈br〉(Jung, H.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0037.pdf"〉Bemerkungen zu den Ausführungen von H. Jung〈/a〉〈br〉(Ansel, E.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0038.pdf"〉Mitteilungen〈/a〉〈br〉(Linke, F.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0040.pdf"〉Wesensgleiche und wesensverschiedene Darstellungen〈/a〉〈br〉(Nippoldt, A.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0041.pdf"〉Die Säkularvariation in der Rheinpfalz in den Jahren 1850 bis 1928〈/a〉〈br〉(Burmeister, F.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0042.pdf"〉Größenverhältnis von remanentem zu induziertem Magnetismus in Gesteinen; Größe und Richtung des remanenten Magnetismus〈/a〉〈br〉(Koenigsberger, J.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0043.pdf"〉Über eine magnetische Anomalie am Lebasee in Ostpommern〈/a〉〈br〉(Reich, H.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0045.pdf"〉Die Ergebnisse der magnetischen Messungen in der Ostsee in den Jahren 1924 bis 1929〈/a〉〈br〉(v. Gernet-Reval, A.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0047.pdf"〉Erdmagnetische Messungen in Bulgarien, Mazedonien, Trazien und in der Dobrudja〈/a〉〈br〉(Popoff, K.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0048.pdf"〉Einige Bemerkungen über erdmagnetische Messungen, welche in Feodossia ausgeführt wurden〈/a〉〈br〉(Palazzo, L.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0049.pdf"〉Possible causes of abnormal polarizations of magnetic formations〈/a〉〈br〉(Heiland, C.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0050.pdf"〉Die geologische Bedeutung der Schaffung einer Isanomalenkarte der magnetischen Vertikalintensität von Deutschland〈/a〉〈br〉(Schuh, F.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0051.pdf"〉Die innere Genauigkeit von Inklinationsmessungen mit dem Erdinduktor〈/a〉〈br〉(Venske, O.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0052.pdf"〉Theorie einer neuen galvanischen Waage〈/a〉〈br〉(Bock, R.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0053.pdf"〉Messungen im Luftschiff〈/a〉〈br〉(Haussmann, K.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0054.pdf"〉Une modification de l'enregistreur à marche rapide et à petite consommation de papier de Ad. Schmidt pour l'application aux stations de l'Anneé Polaire 1932–1933〈/a〉〈br〉(la Cour, D.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0056.pdf"〉Was sagen uns die Parameter eines Magneten?〈/a〉〈br〉(Fanselau, G.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0057.pdf"〉Über die Herleitung des Potentials des täglichen erdmagnetischen Variationsfeldes〈/a〉〈br〉(Egedal, J.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0058.pdf"〉Über den Vektor der magnetischen Störungen im aperiodischen Verlauf〈/a〉〈br〉(Keränen, J.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0059.pdf"〉Forschungsmethode über den Zusammenhang zwischen der Sonnenfleckentätigkeit und den erdmagnetischen Störungen〈/a〉〈br〉(Gehlinsch, E.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0060.pdf"〉Der Temperaturverlauf im Sandboden〈/a〉〈br〉(Süring, R.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0061.pdf"〉Die dominierende Luftdruckwelle des strengen Winters 1928/29〈/a〉〈br〉(Weickmann, L.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0063.pdf"〉Über einige meteorologische Begriffe〈/a〉〈br〉(Tetens, O.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0066.pdf"〉Über die Feinstruktur des Temperaturgradienten längs Berghängen〈/a〉〈br〉(Wagner, A.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0067.pdf"〉Das unperiodische Element im Tropenklima〈/a〉〈br〉(Knoch, K.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0068.pdf"〉Zur Theorie der Maxwellschen Geschwindigkeitsverteilung in turbulenten Strömungen〈/a〉〈br〉(Ertel, H.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0069.pdf"〉Wie tief dringen die Polarlichter in die Erdatmosphäre ein?〈/a〉〈br〉(Störmer, C.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0072.pdf"〉Gammastrahlen an Kaliumsalzen〈/a〉〈br〉(Kolhörster, W.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0073.pdf"〉Über die Form der Fernschallwelle〈/a〉〈br〉(Kühl, W.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0074.pdf"〉Die Seismizität des Südantillenbogens〈/a〉〈br〉(Tams, E.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0076.pdf"〉Eine neue württembergische Erdbebenwarte〈/a〉〈br〉(Kleinschmidt, E.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0077.pdf"〉Über den Zusammenhang zwischen Typhusmorbidität (bzw. Typhusmortalität) und Niederschlagsschwankungen nebst einer Kritik der Brücknerschen Klimaperiode〈/a〉〈br〉(Wenzel Pollak, L.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0079.pdf"〉Über die Abhängikeit der Schwerkraft vom Zwischenmedium〈/a〉〈br〉(Schlomka, T.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0080.pdf"〉On the Determination of the Lunar Atmospheric Tide〈/a〉〈br〉(Chapman, S.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0081.pdf"〉Die Wärmeumsatz durch die Wärmestrahlung des Wasserdampfes in der Atmosphäre〈/a〉〈br〉(Albrecht, F.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0082.pdf"〉Ein Universal-Induktionsmagnetometer〈/a〉〈br〉(Uljanin, W.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0083.pdf"〉Der große Staubfall vom 26. bis 29. April 1928 in Südosteuropa〈/a〉〈br〉(Stenz, E.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0085.pdf"〉Ein neues Verfahren der luftelektrischen Raumladungsmessung〈/a〉〈br〉(Wigand, A., Schubert, J., Frankenberger, E.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0086.pdf"〉Kurze Erwiderung auf Vegards Bemerkungen über sonnenbelichtete Nordlichtstrahlen〈/a〉〈br〉(Störmer, C.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0088.pdf"〉Die Invariabilität und Abstimmung von Minimumpendeln〈/a〉〈br〉(Kohlschütter, E.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0089.pdf"〉Bemerkung zu der Arbeit "Die Invariabilität und Abstimmung von Minimumpendeln" von E. Kohlschütter〈/a〉〈br〉(Meisser, O.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0090.pdf"〉Erwiderung〈/a〉〈br〉(Kohlschütter, E.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0091.pdf"〉Bemerkungen zu der Arbeit von Herrn Dr. O. Meisser: "Ein neuer Vierpendelapparat für relative Schweremessungen"〈/a〉〈br〉(Heiland, C.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0092.pdf"〉Bemerkungen zu den vorstehenden Ausführungen von Herrn Prof. Dr. C. A. Heiland〈/a〉〈br〉(Meisser, O.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0093.pdf"〉Das Epizentrum des südatlantischen Großbebens vom 27. Juni 1929〈/a〉〈br〉(Tams, E.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0094.pdf"〉Seismische Untersuchungen auf dem Pasterzegletscher. I〈/a〉〈br〉(Brockamp, B., Mothes, H.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0096.pdf"〉Bericht über die neunte Tagung der Deutschen Geophysikalischen Gesellschaft vom 11. bis 14. September 1930 in Potsdam〈/a〉〈br〉(Mügge, Linke, F.)〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0097.pdf"〉Autorenverzeichnis〈/a〉〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0098.pdf"〉Sachverzeichnis〈/a〉〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0099.pdf"〉Literaturverzeichnis〈/a〉〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0100.pdf"〉Geophysikalische Berichte〈/a〉〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0101.pdf"〉Register der Geophysikalischen Berichte〈/a〉〈/li〉 〈li〉〈a href="https://gdz.sub.uni-goettingen.de/download/pdf/PPN101433392X_0006/LOG_0102.pdf"〉Mitgliederverzeichnis der Deutschen Geophysikalischen Gesellschaft nach dem Stande vom 1. Oktober 1930〈/a〉〈/li〉 〈/body〉 〈/html〉

Description: research

Description: DGG, DFG, SUB Göttingen

Description: Large-eddy simulations are performed using wall-resolved mesh for a Mach 2.29 impinging shock wave/boundary-layer interaction. Flow conditions are based on an experiment and therefore entire span was simulated, including the two sidewalls. Mean flow comparison with the experimental data showed that the predicted interaction length was larger in the simulation. Time-series analysis of a rake of pressure signals immediately downstream of the mean reflected shock position showed a peak in weighted power spectral density occurred about St(sub Lint) = 0.01, owing to a larger interaction length. Budgets of Reynolds-stress transport calculated across the span and along the corner bisector showed high degree of anisotropy. Merging of the secondary flows and separation along the corner gave rise to unstable counter-rotating vortices, which straddle the corner and grow in size. This also leads to a development of new behavior in the viscous sublayer along the corner bisector, where the pressure strain and molecular diffusion mechanisms become prominent.

Description: No abstract available

Description: No abstract available

Description: This is a 20 minute presentation discussing the DELIVER vision. DELIVER is part of the ARMD Transformative Aeronautics Concepts Program, particularly the Convergent Aeronautics Solutions Project. The presentation covers the DELIVER vision, transforming markets, conceptual design process, challenges addressed, technical content, and FY2016 key activities.

Description: Large-eddy simulations are performed using wall-resolved mesh for a Mach 2.29 impinging shock wave/boundary-layer interaction. Flow conditions are based on an experiment and therefore entire span was simulated, including the two sidewalls. Mean flow comparison with the experimental data showed that the interaction was larger in the simulation. Time-series analysis of a rake of pressure probes immediately downstream of the mean reflected shock position showed a peak in weighted power spectral density occurred about $St_{Lint}=0.01$, owing to a larger interaction length. Budgets of Reynolds-stress transport calculated across the span and along the corner bisector showed high degree of anisotropy. Merging of the secondary flows and separation along the corner gives rise to unstablecounter rotating vortices, which straddle the corner and grow in size. This also leads to a development of new behavior in the viscous sublayer along the corner bisector, where the pressure strain andmolecular diffusion mechanisms become prominent.

Description: The main goal of this study is to examine the impact of new trends in satellite launch activities on the orbital debris environment and collision risk. Starting from the launch of the first artificial satellite in 1957, space borne technology has become an indispensable part of our lives. More than 6,000 satellites have been launched into Earth orbit. Though the annual number of satellites launched stayed flat for many decades, the trend has recently changed. The satellite market has been undergoing a major evolution with new space companies replacing the traditional approach of deploying a few large, complex and costly satellites with an approach to use a multitude of smaller, less complex and cheaper satellites. This new approach creates a sharp increase in the number of satellites and so the historic trends are no longer representative. As a foundation for this study, a scenario for satellite deployments based on the publicly announced future satellite missions has been developed. These constellation-deploying companies include, but are not limited to, Blacksky, CICERO, EROS, Landmapper, Leosat, Northstar, O3b, OmniEarth, OneWeb, Orbcomm, OuterNet, PlanetIQ, Planet Labs, Radarsat, RapidEye Next Generation, Sentinel, Skybox, SpaceX, and Spire. Information such as the annual number of launches, the number of orbital planes to be used by the constellation, as well as apogee, perigee, inclination, spacecraft mass and area were included or approximated. Besides the production of satellites, a widespread ongoing effort to enhance orbital injection capabilities will allow delivery of more spacecraft more accurately into Earth orbits. A long list of companies such as Microcosm, Rocket Lab, Firefly Space Systems, Sierra Nevada Corporation and Arca Space Corporation are developing new launch vehicles dedicated for small satellites. There are other projects which intend to develop interstages with propulsive capabilities which will allow the deployment of satellites into their desired orbits beyond the restrictions of the launch vehicle used. These near future orbital injection technologies are also covered in the developed scenario. Using the above-mentioned background information, this study aims to examine how the orbital debris environment will be affected from the new dynamics of the emerging space markets. We developed a simulation tool that is capable of propagating the objects in a given deployment scenario with variable-sized time-steps as small as one second. Over the course of the run, the software also detects collisions; additional debris objects are then created according to the NASA breakup model and are fed back into the simulation framework. Examining the simulation results, the total number of particles to accumulate in different orbits can be monitored and the number of conjunctions can be tracked to assess the collision risks. The simulation makes it possible to follow the short- and long-term effects of a particular satellite or constellation on the space environment. Likewise, the effects of changes in the debris environment on a particular satellite or constellation can be evaluated. It is authors hope that the results of this paper and further utilization of the developed simulation tool will assist in the investigation of more accurate deorbiting metrics to replace the generic 25-year disposal guidelines, as well as to guide future launches toward more sustainable and safe orbits.

Description: Abstract:We exercise the computational fluid dynamics code OVERFLOW on sixteen turbulence model validation cases from the NASALangley Turbulence Model Resource web site. We give some information about the OVERFLOW options used to run these cases, and compare OVERFLOW results with results from other codes and with experiment. The goal is turbulence model validation for OVERFLOW.

Description: Temperature-dependent data of a RUAG six-component block-type balance was analyzed to assess the accuracy of two load prediction methods for temperature-dependent balance data. The supplied data was prepared for the analysis by splitting it into calibration and check load data subsets. The first calibration data subset was obtained at a temperature of 294 Kelvin. The second calibration data subset was obtained at a temperature of 315 Kelvin. A subset of 38 points was extracted from the second data set and used as check loads so that the accuracy of the two load prediction methods could be tested. First, the Iterative Method in combination with an extended independent and dependent variable set was used for the balance load prediction. This approach fits electrical outputs as a function of loads and the temperature and, afterwards, constructs a load iteration scheme from the regression coefficients so that loads can be predicted from outputs and the temperature during a wind tunnel test. The Non-Iterative Method was also used for the load prediction. This alternate method can more easily be implemented in a data system as loads are directly fitted as a function of electrical outputs and the temperature. Analysis results for the axial force are only discussed in the paper as similar results were obtained for the other five load components. Results for both methods clearly show that the cross-product term constructed from either a primary gage load or a primary gage output and the temperature explains the majority of the temperature-dependent part of the predicted balance load. This term models the temperature dependent nature of the gage sensitivity. Therefore, it is recommended to apply primary gage loadings at different temperatures during a balance calibration whenever temperature effects need to be described. These loadings will contain information about the temperature-dependent nature of the gage sensitivities that can be quantified by related cross-product terms in regression models of the data.

Description: An overview of UTM (UAS (Unmanned Aircraft Systems) Traffic Management) and UAM (Urban Air Mobility).

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Description: An overview of NASA GRC and how it is advancing exploration of our solar system and beyond while maintaining global leadership in aeronautics.

Description: A guiding principle for conducting research in technology, science, and engineering, leading to innovation is based on our use of research methodology (both qualitative and qualitative). A brief review of research methodology will be presented with an overview of NASA process in developing aeronautics technologies and other things to consider in research including what is innovation.

Description: A quantitative global skin-friction measurement technique is proposed. An oil-film is doped with a luminescent molecule and thereby made to fluoresce in order to resolve oil-film thickness, and Particle Image Surface Flow Visualization is used to resolve the velocity field of the surface of the oil-film. Skin-friction is then calculated at location x as (x )xh, where x is the displacement of the surface of the oil-film and is the dynamic viscosity of the oil. The data collection procedure and data analysis procedures are explained, and preliminary experimental skin-friction results for flow over the wing of the CRM are presented.

Description: As Unmanned Aircraft Systems (UAS) make their way to mainstream aviation operations within the National Airspace System (NAS), research efforts are underway to develop a safe and effective environment for their integration into the NAS. Detect and Avoid (DAA) systems are required to account for the lack of "eyes in the sky" due to having no human on-board the aircraft. The current NAS relies on pilot's vigilance and judgement to remain Well Clear (CFR 14 91.113) of other aircraft. RTCA SC-228 has defined DAA Well Clear (DAAWC) to provide a quantified Well Clear volume to allow systems to be designed and measured against. Extended research efforts have been conducted to understand and quantify system requirements needed to support a UAS pilot's ability to remain well clear of other aircraft. The efforts have included developing and testing sensor, algorithm, alerting, and display requirements. More recently, sensor uncertainty and uncertainty mitigation strategies have been evaluated. This paper discusses results and lessons learned from an End-to-End Verification and Validation (E2-V2) simulation study of a DAA system representative of RTCA SC-228's proposed Phase I DAA Minimum Operational Performance Standards (MOPS). NASA Langley Research Center (LaRC) was called upon to develop a system that evaluates a specific set of encounters, in a variety of geometries, with end-to-end DAA functionality including the use of sensor and tracker models, a sensor uncertainty mitigation model, DAA algorithmic guidance in both vertical and horizontal maneuvering, and a pilot model which maneuvers the ownship aircraft to remain well clear from intruder aircraft, having received collective input from the previous modules of the system. LaRC developed a functioning batch simulation and added a sensor/tracker model from the Federal Aviation Administration (FAA) William J. Hughes Technical Center, an in-house developed sensor uncertainty mitigation strategy, and implemented a pilot model similar to one from the Massachusetts Institute of Technology's Lincoln Laboratory (MIT/LL). The resulting simulation provides the following key parameters, among others, to evaluate the effectiveness of the MOPS DAA system: severity of loss of well clear (SLoWC), alert scoring, and number of increasing alerts (alert jitter). The technique, results, and lessons learned from a detailed examination of DAA system performance over specific test vectors and encounter cases during the simulation experiment will be presented in this paper.

Description: The integrated Flight Test 4 (FT4) will gather data for the UAS researchers Sense and Avoid systems (referred to as Detect and Avoid in the RTCA SC 228 ToR) algorithms and pilot displays for candidate UAS systems in a relevant environment. The technical goals of FT4 are to: 1) perform end-to-end traffic encounter test of pilot guidance generated by DAA algorithms; 2) collect data to inform the initial Minimum Operational Performance Standards (MOPS) for Detect and Avoid systems. FT4 objectives and test infrastructure builds from previous UAS project simulations and flight tests. NASA Ames (ARC), NASA Armstrong (AFRC), and NASA Langley (LaRC) Research Centers will share responsibility for conducting the tests, each providing a test lab and critical functionality. UAS-NAS project support and participation on the 2014 flight test of ACAS Xu and DAA Self Separation (SS) significantly contributed to building up infrastructure and procedures for FT3 as well. The DAA Scripted flight test (FT4) will be conducted out of NASA Armstrong over an eight-week period beginning in April 2016.

Description: A likely scenario for swept wing transition on subsonic aircraft with natural laminar flow involves the breakdown of stationary crossflow vortices via high frequency secondary instability. A majority of the prior research on this secondary instability has focused on crossflow vortices with a single dominant spanwise wavelength. This paper investigates the effects of the spanwise modulation of stationary crossflow vortices at a specified wavelength by a subharmonic stationary mode. Secondary instability of the modulated crossflow pattern is studied using planar, partial-differential-equation based eigenvalue analysis. Computations reveal that weak modulation by the first subharmonic of the input stationary mode leads to mode splitting that is particularly obvious for Y-type secondary modes that are driven by the wall-normal shear of the basic state. Thus, for each Y mode corresponding to the fundamental wavelength of results in unmodulated train of crossflow vortices, the modulated flow supports a pair of secondary modes with somewhat different amplification rates. The mode splitting phenomenon suggests that a more complex stationary modulation such as that induced by natural surface roughness would yield a considerably richer spectrum of secondary instability modes. Even modest levels of subharmonic modulation are shown to have a strong effect on the overall amplification of secondary disturbances, particularly the Z-modes driven by the spanwise shear of the basic state. Preliminary computations related to the nonlinear breakdown of these secondary disturbances provide interesting insights into the process of crossflow transition in the presence of the first subharmonic of the dominant stationary vortex.

Description: Multicopters are becoming one of the more common and popular type of unmanned aircraft systems (UAS) which have both civilian and military applications. One example being the concept of drone deliveries proposed by the distribution company Amazon [1]. The electrical propulsion is considered to have both faster and easier deliveries and also environmental benefits compared to other vehicles that still use fossil fuel. Other examples include surveillance and just simple entertainment. The reason behind their success is often said to be due to their small size, relatively low cost, simple structure and finally simple usage. With an increase in the UAS market comes challenges in terms of security, as both people and other aircrafts could be harmed if not used correctly. Therefore further studies and regulations are needed to ensure that future use of drones, especially in the civilian and public sectors, are safe and efficient. Thorough research has been done on full scale, man or cargo transporting, helicopters so that most parts of flight and performance are fairly well understood. Yet not much of it have been verified for small multicopters. Until today many studies and research projects have been done on the control systems, navigation and aerodynamics of multicopters. Many of the methods used today for building multicopters involve a process of trial an error of what will work well together, and once that is accomplished some structural analysis of the multicopter bodies might be done to verify that the product will be strong enough and have a decent aerodynamic performance. However, not much has been done on the research of the rotor blades, especially in terms of structural stress analyses and ways to ensure that the commonly used parts are indeed safe and follow safety measures. Some producers claim that their propellers indeed have been tested, but again that usually tends towards simple fluid dynamic analyses and even simpler stress analyses. There is no real deflection measurement of said blades and all theory is today based on the theory developed for full scale helicopters. This report thus intends to highlight the problems that come with blade deflection theory and measurements for multicopters. This thesis starts with the introduction and problem formulation where the grounds for what the report contains are laid out. Then a literature review of the research within the area follows where previous and current research and methods are presented. In the background information and theory relevant to the area are presented. After that the methods and set up of the different experimental and computer simulation approaches are depicted. In the results section the obtained results are presented and compared. Lastly there is a discussion where the results and methods are evaluated and analyzed, followed by the most important conclusions.

Description: Vibration-based condition indicators continue to be developed for Health Usage Monitoring of rotorcraft gearboxes. Testing performed at NASA Glenn Research Center have shown correlations between specific condition indicators and specific types of gear wear. To speed up the detection and analysis of gear teeth, an image detection program based on the Viola-Jones algorithm was trained to automatically detect spiral bevel gear wear pitting. The detector was tested using a training set of gear wear pictures and a blind set of gear wear pictures. The detector accuracy for the training set was 75 percent while the accuracy for the blind set was 15 percent. Further improvements on the accuracy of the detector are required but preliminary results have shown its ability to automatically detect gear tooth wear. The trained detector would be used to quickly evaluate a set of gear or pinion pictures for pits, spalls, or abrasive wear. The results could then be used to correlate with vibration or oil debris data. In general, the program could be retrained to detect features of interest from pictures of a component taken over a period of time.

Description: The 9- by 15-Foot Low Speed Wind Tunnel has been used for acoustic testing for more than 40 years. The facility is principally used for testing aircraft engine propulsion components, for both aerodynamic performance and acoustics. The present report discusses the instrumentation and procedures currently used for the acquisition of high-quality acoustic data from aircraft engine fan models.

Description: There is renewed interest in developing new supersonic transports after the discontinuation of the Concorde supersonic jet, which was mostly limited for flights over trans-oceanic routes due to the severe noise of the sonic boom. In order to avoid the sonic boom, more slender configurations, such as the Low Boom Flight Demonstrator (LBFD) configuration, are being considered. The aeroelastic characteristics of these new supersonic transports can significantly differ from conventional aircraft. Both rigid and flexible body modes can play a significant role in aeroelastic stability. For unconventional configurations, such as aircraft with forward swept wings, the short period oscillation (SPO) has been found to significantly impact the aeroelastic response. SPO can occur due to unanticipated events such as gusts, abrupt maneuvering, etc. During the design of the Concorde, the effects of SPO was considered in detail, though its impact is not publically disclosed. Assuring stability of supersonic aircraft, particularly during descent from the supersonic Mach regime to the transonic regime, is critical. An aircraft can deviate from its normal descent trajectory due to coupling between flows and body motions. The effect of SPO needs to be considered in aeroelastic responses. Preliminary studies using quasi-steady aerodynamics show that the presence of SPO can lead to unstable response. The well-established Reynolds Averaged Navier-Stokes (RANS) equations, which are computationally feasible with current supercomputers, have been in use for aeroelastic computations for the last three decades. Recently, such efforts have begun to include trajectory motions; for instance, the effect of phugoid motion on stability is studied in Ref. 9 using the RANS equations. In this paper, the effect of SPO on aeroelastic responses of a typical supersonic transport is studied.

Description: In 2015, the National Aeronautics and Space Administration (NASA) formed a multi-center, interdisciplinary team of engineers from three different aeronautics research centers who were tasked with improving NASA autonomy research capabilities. This group was subsequently named the Aeronautics Autonomy Testbed Capability (AATC) team. To aid in confronting the autonomy research directive, NASA contracted IDEO, a design firm, to provide consultants and guides to educate NASA engineers through the practice of design thinking, which is an unconventional method for aerospace design processes. The team then began learning about autonomy research challenges by conducting interviews with a diverse group of researchers and pilots, military personnel and civilians, experts and amateurs. Part of this design thinking process involved developing ideas for products or programs known as concepts that could enable real world fulfillment of the most important latent needs identified through analysis of the interviews. The concepts are intended to be sacrificial, intermediate steps in the design thinking process and are presented in this report to record the efforts of the AATC group. Descriptions are provided in present tense to allow for further ideation and imagining the concept as reality as was attempted during the teams discussions and interviews. This does not indicate that the concepts are actually in practice within NASA though there may be similar existing programs independent of AATC. These concepts were primarily created at two distinct stages during the design thinking process. After the initial interviews, there was a workshop for concept development and the resulting ideas are shown in this work as from the First Round. As part of succeeding interviews, the team members presented the First Round concepts to refine the understanding of existing research needs. This knowledge was then used to generate an additional set of concepts denoted as the Second Round. Some concepts were created by a single person in a few minutes while others were refined by the entire team over several weeks. Thus, certain ideas are more detailed than others but those from the second round are not necessarily more comprehensive than the first round concepts. Primarily, as reported here in the Second Round section, the designs serve to encompass more of the high level end user research needs which were not necessarily known to the team during the prior workshop. In the figures provided throughout this report, illustrations are often provided to represent a concept. Nearly all of the images are informal sketches or renderings and this casualness should, hopefully, not be held to negate the potential insights available within the concepts.

Description: The purpose of this document is to introduce a new user to the procedures for overset CFD analysis by building scripts based on the CGT Script Library. Parameterized inputs are built into the steps of the process which include creation and manipulation of geometry, and surface and volume meshing. In preparation for performing computations in the flow solver, further steps are constructed for specification of inputs for domain connectivity, flow solver boundary conditions, and components for computation of aerodynamic forces/moments. The JCLV rocket will be used as an example geometry for this demonstration.

Description: I am honored to endorse the 2015 Neil A. Armstrong Flight Research Centers Research, Technology, and Engineering Report. The talented researchers, engineers, and scientists at Armstrong are continuing a long, rich legacy of creating innovative approaches to solving some of the difficult problems and challenges facing NASA and the aerospace community.Projects at NASA Armstrong advance technologies that will improve aerodynamic efficiency, increase fuel economy, reduce emissions and aircraft noise, and enable the integration of unmanned aircraft into the national airspace. The work represented in this report highlights the Centers agility to develop technologies supporting each of NASAs core missions and, more importantly, technologies that are preparing us for the future of aviation and space exploration.We are excited about our role in NASAs mission to develop transformative aviation capabilities and open new markets for industry. One of our key strengths is the ability to rapidly move emerging techniques and technologies into flight evaluation so that we can quickly identify their strengths, shortcomings, and potential applications.This report presents a brief summary of the technology work of the Center. It also contains contact information for the associated technologists responsible for the work. Dont hesitate to contact them for more information or for collaboration ideas.

Description: The Layered and Extensible Aircraft Performance System (LEAPS) is a new sizing and synthesis tool being developed within the Aeronautics Systems Analysis Branch (ASAB) at NASA Langley Research Center. It is a modular, multidisciplinary, multi- fidelity sizing and synthesis tool for modeling advanced aircraft concepts and architectures such as electric/hybrid-electric propulsion, unconventional propulsion airframe integration, and non-traditional mission trajectories. The development of LEAPS is motivated by the lack of existing tools that meet the needs of ASAB. The Flight Optimization System (FLOPS) has been the primary sizing and synthesis tool of ASAB for three decades. However, FLOPS has a number of limitations that make it dicult to use for unconventional aircraft designs. Three high-level goals have been adopted to guide the LEAPS development pro- cess. LEAPS is being developed in Python with an architecture built to enable a exible and extensible analysis capability using the concept of an aircraft object that combines data and analysis models. Five challenge problems for LEAPS have been identi ed to measure progress: analysis of a conventional tube-and-wing aircraft using legacy methods, coupled aeroelastic analysis for weight estimation of a conventional tube-and-wing aircraft, analysis of an advanced hybrid-electric concept, analysis of the X-57 Maxwell distributed electric propulsion aircraft, and optimization of the trajectory of a supersonic vehicle to minimize sonic boom. LEAPS will be a publicly available capability of exceptional quality with modularity and extensibility that makes it a robust tool for design and analysis of current and future unconventional aircraft concepts.

Description: Future urban mobility promises to deliver transformative impact across the value chain. Consequently, suppliers will face disruption in the form of new technologies, stakeholders and market dynamics. How can supply networks be optimized to meet capabilities that are yet unknown? This session will explore what business models and supply chain strategies can best deliver value for urban air transport and will address how to scale these networks at the pace of this rapidly evolving ecosystem.

Description: Turbulent flows have a large range of spatial and temporal scales which need to be resolved in order to obtain accurate predictions. Higher-order methods can provide greater efficiency for simulations requiring high spatial and temporal resolution, allowing for solutions with fewer degrees of freedom and lower computational cost than traditional second-order computational fluid dynamics (CFD) methods.1 Higher-order methods have been widely used for turbulent flows. However, the reduced numerical stabilization present in higher-order schemes implies that special care needs to be taken in the development of numerical methods to suppress nonlinear instabilities.26 In this work we present the development of a higher-order space-time discontinuous Galerkin method with a focus on the aspects of our numerical scheme required for ensuring nonlinear stability for turbulent simulations at high Reynolds numbers.

Description: Results are presented for four optimization benchmark problems posed by the AIAA Aerodynamic Design Optimization Discussion Group. The benchmarks are intended to exercise optimization frameworks on representative airfoil and wing design problems. All problems involve drag minimization subject to geometric and aerodynamic constraints. Our design approach involves two forms of adaptation. First, the shape parameterization is gradually and automatically enriched from an initially coarse search space. Second, adjoint solutions are used to drive adaptive mesh refinement to control discretization error. The error threshold is tailored so that the nest meshes, with the greatest accuracy, are used only when nearing the optimum. On the inviscid airfoil design problem, while reducing the drag by a factor of 10, we show how the combination of progressive parameterization and tiered discretization error control can dramatically accelerate the optimization. On the viscous airfoil design problem, we use inviscid analysis-driven optimization to reduce the total drag by a factor of two. Next, we improve the span efficiency factor of a wing by performing twist optimization. Finally, we optimize the Common Research Model wing, managing to hold drag roughly fixed, while targeting an initially-violated pitching moment constraint. Our approach aims to introduce greater complexity and accuracy only when necessary to improve the design, and also support a greater degree of automation.

Description: As a precursor to studying the acoustics of a coaxial rotor system, the aerodynamics and flow field of a coaxial rotor were simulated to better understand the interaction between the two rotors. RotUNS, an unsteady Navier-Stokes solver that uses a simplified blade aerodynamics model, was used to predict coaxial rotor performance in hover and forward flight. RotUNS steady hover calculations showed improved performance compared to blade element momentum theory. Prior to examining the complex 3D flow field of a coaxial rotor in detail, two airfoils traveling in opposite directions with a vertical separation distance equivalent to the separation between the upper and lower rotor of the coaxial system were simulated. The pressure field generated by the two airfoils aided our interpretation of the more complex coaxial rotor system flow field. The pressure fields above, between, and below the coaxial rotor system were then examined for different azimuth positions of the upper and lower rotor blades.

Description: A brief update of the progress towards RVLT Milestone L490 Initial acoustic model for kW class electric motors. A quiet loading device has been created that will allow for acoustic testing of a motor with different loads applied. Testing has also begun on a larger motor, the Scorpion SII-4020. Description of the installation of this motor as well as initial measurements reported. These include acoustic spectra and beamforming for source localization.

Description: The blades of coaxial, contra-rotating rotor systems cross each other in close proximity and at high relative speeds. This crossing event is a potential source of noise and severe blade loads. Effects of compressibility can aggravate the interaction and significantly alter the pressure field signature and phase relationships. A 2-D analysis of this phenomenon is performed by simulating two airfoils passing each other at specified speeds and vertical separation distances. Several test cases spanning a relevant range of Reynolds numbers, angles of attack, and relative Mach number are considered. The Mach number is varied to simulate the radial variation of velocity from the root to tip of a rotor blade to capture the pressure signature, lift, and drag of the airfoils. The velocity and pressure distributions on the airfoils, and in the space between the airfoils are computed before, at, and after airfoil crossing. The variations of lift and drag coefficients through the interaction are captured. The upper airfoil experiences an increase in lift followed by a very sharp drop in lift during the interaction. When relative Mach numbers are transonic, the region of interaction is greatly extended, with shock interactions occurring. The results show the complex nature of the aerodynamic and fluid dynamic impulses generated by blade-blade interactions, with implications to aeroelastic loads and aeroacoustic sources.

Description: Ground based experiments are often used to understand and measure rotor and airframe aerodynamic performance; however, these experiments have certain limitations. The effects of these limitations are evaluated here using computational fluid dynamic (CFD) modeling techniques. Through this study, data from the 7- by 10-Foot Wind Tunnel experiments of the Large Civil Tilt Rotor (LCTR) at NASA Ames Research Center is validated using CFD. The Reynolds Averages Navier-Stokes solver, RotCFD, is used for the computations. In particular, the effect of the blockage generated by the test hardware on the walls is investigated. To study this problem, simplified geometries such as a flat plate, cube and cylinder are also investigated for blockage effects. This is done to explore if these different geometries can represent the LCTR as a simplified case to reduce computational time and get a quick first understanding of tunnel blockage effects. The focus of this research is to understand the limitations and accuracy of the recent small-scale Large Civil Tilt Rotor wind tunnel test campaigns.

Description: This presentation discusses high-level capabilities and interests in autonomy at NASA Ames, and describes some methods for collaboration.

Description: In response to a NASA request, Heathcoat Fabrics Limited has woven a new parachute fabric (Custom Design 1 G-60315-1800-Q01). This fabric was tested to obtain its permeability in air (i.e., flow-through volume of air per area per time) over a range of differential pressures from 0.146 to 25 psf (7 to 1197 Pa). The fabric met its specification permeability of 60 to 100 ft3/ft2/min (30.5 to 50.8 cm3/cm2/s) at the U.S. standard differential pressure of 0.5 inch of water (2.60 psf, 124 Pa). The permeability results were transformed into an effective porosity model for use in calculations related to the total porosity of parachutes. The tested fabric is being considered for use in parachutes for future missions to Mars. Calculations of drag coefficient were performed for two geometrically identical parachutes using either the new fabric or fabric woven to Parachute Industry Specification PIA-C-7020D Type I (Mars Science Laboratory Disk-Gap-Band parachute operating on Mars at a Mach number of 0.41). These calculations indicate essentially no difference in the drag coefficient between the two parachutes.

Description: An overview of the NASA Advanced Air Transport Technology (AATT) Project and interest inboundary layer transition modeling for future aircraft and propulsion systems is presented.

Description: Uncertainties in early observations of potentially hazardous asteroids result in preliminary impact corridors that can stretch across large portions of the Earths surface. At this early stage of detection, the corridor width and potential for damage are typically estimated using techniques from nuclear weapons research. These estimates often employ spherical blast assumptions resulting in a constant width impact corridor. In actuality, however, the ground damage footprint of obliquely entering asteroids is generally roughly elliptical or butterfly shaped, with the major axis extending in the cross range direction and the minor axis aligned with ground-track of the meteoroid. Since actual ground footprints for oblique entries may have aspect ratios greater than two or three, the assumption of a circular blast may significantly underestimate the area of the impact swath and the at-risk population. This work develops an engineering model that can be used to quickly estimate the eccentricity of the ground footprint as a function of local impact parameters. This yields vastly improved local estimates of the corridor width and can significantly enhance the accuracy of risk analysis.

Description: ASA & Ames Introduction: Overview of NASA and Ames Research Activities, with a special focus on NASA Aeronautics activities. All materials are overview in nature and have been presented previously in open forums.

Description: NASA & Ames Introduction: Overview of NASA and Ames Research Activities, with a special focus on NASA Aeronautics activities. All materials are overview in nature and have been presented previously in open forums.

Description: This paper considers the control of coupled aeroelastic aircraft model with Variable Camber Continuous Trailing Edge Flap (VCCTEF) system. The relative motion between two adjacent flaps is constrained and this actuation constraint problem is converted into an output covariance constraint problem, and therefore can be formulated using linear matrix inequalities (LMIs). A set of LMI conditions is derived for the design of an observer-based dynamic output feedback controller for VCCTEF configured aeroelastic aircraft model. The proposed controller is then applied to the NASA Generic Transport Model (GTM) for simulation, and the results demonstrate the efficacy of the proposed approach.

Description: With the recent interest in Martian exploration using Unmanned Aerial Vehicles (UAV), an experimental study was conducted to investigate rotor performance at Martian atmospheric conditions. Both simulation and testing of rotors is vital for the evaluation of performance and behavior of a rotor, especially when subjected to a Marian atmosphere. One critical test that has not been performed to date is simulated helicopter forward flight in a Martian atmosphere. To achieve this, the test must be conducted in a facility which can be evacuated to the atmospheric pressure and density of Mars. A unique 40-in diameter rotor, roughly approximating a proposed design for a Mars Helicopter (MH), was tested in forward flight at Mars atmospheric pressure at the NASA Ames Planetary Aeolian Laboratory (PAL). The goal of this experiment was to collect rotor thrust, RPM, power, torque, and acoustics measurements. Subsequently, these results are compared with simulated cases using a mid-fidelity Computational Fluid Dynamics (CFD) approach. As expected, rotor thrust and power results are drastically reduced when under low atmospheric conditions. In addition, Reynolds number effects seem to play a vital role that cannot be neglected.

Description: No abstract available

Description: This PowerPoint presentation will discuss Aura's current spacecraft and instrument status, highlight any performance trends and impacts to operations, identify any operational changes and express concerns or potential process improvements. Reviewed by Eric Moyer, ESMO Deputy Project Manager.

Description: Computational simulations using structured overset grids with the Launch Ascent and Vehicle Aerodynamics (LAVA) solver framework are presented for predicting oblique shock/plume interaction effects to near-field sonic boom signatures. Standard second-order accurate as well as higher-resolution numerical discretizations are utilized and compared in the study. The numerical approach is compared with supersonic wind-tunnel data for three cases. The cases include an empty wind-tunnel at the operating conditions, an isolated shockgenerating diamond wedge within the tunnel, and a nozzle with diamond wedge configuration at five different nozzle pressure ratios. Solution sensitivity to numerical discretization is analyzed. Favorable comparisons between the computational results and experimental data of near-field pressure signatures are obtained. A simple prediction method for plume induced shock deflection is developed and results are compared with the CFD data.

Description: The rising number of small unmanned aerial vehicles (UAVs) expected in the next decade will enable a new series of commercial, service, and military operations in low altitude airspace as well as above densely populated areas. These operations may include on-demand delivery, medical transportation services, law enforcement operations, traffic surveillance and many more. Such unprecedented scenarios create the need for robust, efficient ways to monitor the UAV state in time to guarantee safety and mitigate contingencies throughout the operations. This work proposes a generalized monitoring and prediction methodology that utilizes realtime measurements of an autonomous UAV following a series of way-points. Two different methods, based on sinusoidal acceleration profiles and high-order splines, are utilized to generate the predicted path. The monitoring approach includes dynamic trajectory re-planning in the event of unexpected detour or hovering of the UAV during flight. It can be further extended to different vehicle types, to quantify uncertainty affecting the state variables, e.g., aerodynamic and other environmental effects, and can also be implemented to prognosticate safety-critical metrics which depend on the estimated flight path and required thrust. The proposed framework is implemented on a simplified, scalable UAV modeling and control system traversing 3D trajectories. Results presented include examples of real-time predictions of the UAV trajectories during flight and a critical analysis of the proposed scenarios under uncertainty constraints.

Description: No abstract available

Description: A high-lift propeller system is a distributed electric propulsion technology which dedicates an array of wing-mounted tractor propellers to actively augment wing lift during takeoff and landing. This paper describes the results of a wind tunnel experiment dedicated to investigating the effects of high-lift propeller installation geometry on lift generation. Variables investigated include propeller height, offset, and inclination. Results show that propeller height is the most critical variable and that the height for maximum lift depends highly on the angle of attack and flap deflection. In addition, a relationship between optimal propeller height and the wings unblown lift coefficient is discovered.

Description: Previous research and experimentation on the use of a non-linear programming constrained optimisation technique to define an optimal control vector for rotorcraft applications indicated that use of this methodology was feasible and desirable in many cases. In particular, use of non-linear programming methods that solve a sequence of related quadratic-programming sub-problems were used successfully to solve these problems. Accordingly, a licence for one of the latest versions of Professor Klaus Schittkowskis very successful Sequential Quadratic Programming NLPQLP software was obtained and used to experiment with and analyse typical optimisation problems of the type encountered in various rotorcraft wind tunnel and flight tests. This research resulted in the development of the general NLPQLP Computation System that could be used to solve problems of the type encountered in various rotorcraft applications where there is a linear dependence of the measurement vector on the control vector, and where equality andor inequality constraints might be imposed. This development was accomplished on a mainframe computer not part of actual wind tunnel andor flight-test experiment, but in a format which was transferable to wind tunnel lap-top computers. Emphasis was directed toward obtaining efficiency, robustness and speed in computation.The System was developed in support of the five-bladed SMART Rotor Active Flap Rotor Hub Loads analytical minimisation research. The design and development of the Computation System was tailored to address the particular requirements of the problem to minimise a performance metric function of measured hub load harmonic angular couple components by optimising the control vector harmonic flap angular couple components subject to constraints on the amplitudes of these control vector harmonic flap angular couple components. In addition, to facilitate real time wind tunnel experimentation, the ability to rapidly selectchange the particular hub load harmonic angular couple components andor the particular control vector harmonic angular couple components to be considered in the optimisation procedure was provided in the System. This capability allows the singling out of particular hub load frequencies andor particular flap angle frequencies to be analysed during testing operations. The System was used very successfully for the SMART Active Flap Rotor Hub minimisation problems considered in the study, the results of which were presented at the American Helicopter Society Fifth Decennial Aeromechanics Specialist Conference in January 2014. Excellent agreement between cases initiated with best guess starting estimates for the control vector elements and cases initiated with zero control vector starting element estimates resulted, indicating the robustness of the NLP10x10 algorithm.

Description: No abstract available

Description: System safety and resilience is a critical concern in the air traffic domain. An important element of maintaining system safety and resilience is the ability of systems to degrade gracefully. However, previous research on the causes of system degradation in the air traffic domain are sporadic, and the potential interaction between the causes of degradation, and the resulting possible compound effect on the entire system, has been under-researched. An interview study was conducted with 12 retired controllers as participants. The results of a thematic analysis revealed the key causes of system degradation, and the associated impact on the ability of the controllers to prevent system degradation or recover the system. Findings have direct implications for identifying and mitigating potential risks of increasingly automated air traffic control systems.

Description: Downwash and outwash characteristics of a model-scale tandem-rotor system in the presence of the ground were analyzed by identifying and understanding the physical mechanisms contributing to the observed flow field behavior. A building block approach was followed in simplifying the problem, separating the effects of the fuselage, effects of one rotor on the other, etc. Flow field velocities were acquired in a vertical plane at four aircraft azimuths of a small-scale tandem rotor system using the particle image velocimetry (PIV) technique for radial distances up to 4 times the rotor diameter. Results were compared against full-scale CH-47D measurements. Excellent correlation was found between the small- and full-scale mean flow fields (after appropriate normalization using rotor and wall jet parameters). Following the scalability analysis, the effect of rotor height on the outwash was also studied. Close to the aircraft, an increase in rotor height above ground decreased the outwash velocity at all aircraft azimuths. However, farther away, the longitudinal and lateral axes of the aircraft showed increasing and decreasing outwash velocities, respectively, with increasing rotor height. Measurements also indicated the presence of large-scale (of the size of the rotor height) shear-layer vortical structures along the ground that could be the source of low-frequency (approximately 1 Hz) flow variation observed in the full-scale measurements. Flow visualization studies and PIV measurements were also made on jets of different sizes to complement the observations made on rotors wherever possible. Baseline rotor measurements were made out-of-ground effect to understand the nature of inflow distribution for realistic rotor configurations and their modified characteristics in the presence of ground. Lastly, a feasibility study on applying high-fidelity CFD simulations for outwash study was conducted using Helios to model an isolated rotor configuration IGE at full-scale Reynolds number. The results were encouraging and demonstrated the practical challenges associated with predicting rotor outwash.

Description: Carbon preforms used in Thermal Protection System (TPS) materials are 80 to 90% porous, allowing for boundary layer and pyrolysis gases to flow through the porous regions. The bulk material properties such as permeability and hydraulic tortuosity factor affect the transport of the boundary layer gases. The use of Direct Simulation Monte Carlo along with the Klinkenberg permeability formulation allows us to compute the continuum permeability and Knudsen correction factor for flow in the transition regime. In this work, we have computed the permeability for two types of carbon preforms, namely, Morgan Felt and FiberForm, and assessed the effect of orientation on the permeability. Since both the materials are anisotropic, the permeability was found to depend on orientation, wherein, the materials are more permeable in the in-plane orientation than the through-thickness orientation. The through-thickness orientation was also more tortuous compared to the in-plane material orientation. Compared to Morgan Felt, FiberForm is less permeable, in both, through thickness and in-plane directions.

Description: This paper evaluates a thermodynamic ice crystal icing model that has been previously presented to describe the possible mechanisms of icing within the core of a turbofan jet engine. The model functions between two distinct ice accretions based on a surface energy balance: freeze-dominated icing and melt-dominated icing. Freeze-dominated icing occurs when liquid water (from melted ice crystals) freezes and accretes on a surface along with the existing ice of the impinging water and ice mass. This freeze-dominated icing is characterized as having strong adhesion to the surface. The amount of ice accretion is partially dictated by a freeze fraction, which is the fraction of impinging liquid water that freezes. Melt-dominated icing occurs as unmelted ice on a surface accumulates. This melt-dominated icing is characterized by weakly bonded surface adhesion. The amount of ice accumulation is partially dictated by a melt fraction, which is the fraction of impinging ice crystals that melts. Experimentally observed ice growth rates suggest that only a small fraction of the impinging ice remains on the surface, implying a mass loss mechanism such as splash, runback, bounce, or erosion. The fraction of mass loss must be determined in conjunction with the fraction of freezing liquid water or fraction of melting ice on an icing surface for a given ice growth rate. This mass loss parameter, however, along with the freeze fraction and melt fraction, are the only experimental parameters that are currently not measured directly. Using icing growth rates from ice crystal icing experiments, a methodology that has been previously proposed is used to determine these unknown parameters. This work takes ice accretion data from tests conducted by the National Aeronautics and Space Administration (NASA) at the Glenn Research Center in 2018 that examined the fundamental physics of ice crystal icing. This paper continues evaluation of the thermodynamic model from a previous effort, with additions to the model that account for sub-freezing temperatures that have been observed at the leading edge of the airfoil during icing. The predicted temperatures were generally in good agreement with measured temperatures. Other key findings include the total wet-bulb temperature being a good first order indicator of whether icing is freeze-dominated (sub-freezing values) or melt-dominated (above freezing). Maximum sticking efficiency values, the fraction of impinging mass that adheres to a surface, was calculated to be about 0.2, and retained this maximum value for a range of melt ratios (0.3 to 0.65 and possibly higher), which is defined as the ratio of liquid water content to total water content. Higher air velocities reduced the maximum sticking efficiency and shifted the icing regime to higher melt ratio values. Finally, the leading edge ice accretion angle was found to be related to ice growth (lower growth rates for smaller angles) and melt ratio (smaller melt ratios resulted in smaller angles, likely due to erosion effects).

Description: The Honeywell Uncertified Research Engine (HURE), a research version of a turbofan engine that never entered production, was tested in the NASA Propulsion System Laboratory (PSL), an altitude test facility at the NASA Glenn Research Center. The PSL is a facility that is equipped with water spray bars capable of producing an ice cloud consisting of ice particles, having a controlled particle diameter and concentration in the air flow. To develop the test matrix of the HURE, numerical analysis of flow and ice particle thermodynamics was performed on the compression system of the turbofan engine to predict operating conditions that could potentially result in a risk of ice accretion due to ice crystal ingestion. The goal of the test matrix was to have ice accrete in two regions of the compression system: region one, which consists of the fan-stator through the inlet guide vane (IGV), and region two which is the first stator within the high pressure compressor. The predictive analyses were performed with the mean line compressor flow modeling code (COMDES-MELT) which includes an ice particle model. The HURE engine was tested in PSL with the ice cloud over the range of operating conditions of altitude, ambient temperature, simulated flight Mach number, and fan speed with guidance from the analytical predictions. The engine was fitted with video cameras at strategic locations within the engine compression system flow path where ice was predicted to accrete, in order to visually confirm ice accretion when it occurred. In addition, traditional compressor instrumentation such as total pressure and temperature probes, static pressure taps, and metal temperature thermocouples were installed in targeted areas where the risk of ice accretion was expected. The current research focuses on the analysis of the data that was obtained after testing the HURE engine in PSL with ice crystal ingestion. The computational method (COMDES-MELT) was enhanced by computing key parameters through the fan- stator at multiple span wise locations, in order to increase the fidelity with the current mean-line method. The Icing Wedge static wet bulb temperature thresholds were applicable for determining the risk of ice accretion in the fan-stator, which is thought to be an adiabatic region. At some operating conditions near the splitter-lip region, other sources of heat (non-adiabatic walls) were suspected to be the cause of accretion, and the Icing Wedge was not applicable to predict accretion at that location. A simple order-of-magnitude heat transfer model was implemented into the COMDES-MELT code to estimate the wall temperature minimum and maximum thresholds that support ice accretion, as observed by video confirmation. The results from this model spanned the range of wall temperatures measured on a previous engine that experienced ice accretion at certain operating conditions.

Description: Any cluster of parachute systems is subject to effects on performance due to interactions between the parachutes. One such interaction is the twisting of a riser from one parachute around that of another. Due to friction and relative motion between the risers, it is possible for the tension in the riser near the attach point to be different from the tension in the riser towards the suspension lines or canopy. This could result in system failure due to larger than expected loading. The Orion Capsule Parachute Assembly System (CPAS) designed and executed a test to quantify the amplification of the load in a parachute riser due to twist, rocking rate and angle, cluster size, and canopy load. The design of the testing approach, test matrix, and hardware are discussed along with results and findings.

Description: The swirl distortion of a StreamVane (Trademark) was investigated in the NASA Glenn Research Center W8 test facility. The StreamVane (Trademark) was designed and generated by Virginia Tech based on CFD simulations and included a center body at the aerodynamic interface plane. The swirl pattern generated by the distortion was evaluated using a dense grid of 5-hole Pitot probe measurements captured using a rotating array of probes. Good agreement was found between the design intent and the results at 38.5 kg/s mass flow. The StreamVane (Trademark) swirl results were compared to clean facility flow at 5 inlet mass flows and found to be consistent. Additionally, the axial location of the StreamVane (Trademark) relative to the measurement plane was investigated to determine the impact on downstream total pressure loss generated by the vanes. The intent of this work was to assess the viability of using a StreamVane (Trademark) to generate a Type I or Type II distortion into a Boundary Layer Ingesting propulsor to assess its aerodynamic performance and aeromechanic response.

Description: The Honeywell Uncertified Research Engine (HURE), a research version of a turbofan engine that never entered production, was tested in the NASA Propulsion System Laboratory (PSL), an altitude test facility at the NASA Glenn Research Center. The PSL is a facility that is equipped with water spray bars capable of producing an ice cloud consisting of ice particles, having a controlled particle diameter and concentration in the air flow. To develop the test matrix of the HURE, numerical analysis of flow and ice particle thermodynamics was performed on the compression system of the turbofan engine to predict operating conditions that could potentially result in a risk of ice accretion due to ice crystal ingestion. The goal of the test matrix was to have ice accrete in two regions of the compression system: region one, which consists of the fan-stator through the inlet guide vane (IGV), and region two which is the first stator within the high pressure compressor. The predictive analyses were performed with the mean line compressor flow modeling code (COMDES-MELT) which includes an ice particle model. The HURE engine was tested in PSL with the ice cloud over the range of operating conditions of altitude, ambient temperature, simulated flight Mach number, and fan speed with guidance from the analytical predictions. The engine was fitted with video cameras at strategic locations within the engine compression system flow path where ice was predicted to accrete, in order to visually confirm ice accretion when it occurred. In addition, traditional compressor instrumentation such as total pressure and temperature probes, static pressure taps, and metal temperature thermocouples were installed in targeted areas where the risk of ice accretion was expected. The current research focuses on the analysis of the data that was obtained after testing the HURE engine in PSL with ice crystal ingestion. The computational method (COMDES-MELT) was enhanced by computing key parameters through the fan-stator at multiple span wise locations, in order to increase the fidelity with the current mean-line method. The Icing Wedge static wet bulb temperature thresholds were applicable for determining the risk of ice accretion in the fan-stator, which is thought to be an adiabatic region. At some operating conditions near the splitter-lip region, other sources of heat (non-adiabatic walls) were suspected to be the cause of accretion, and the Icing Wedge was not applicable to predict accretion at that location. A simple order-of-magnitude heat transfer model was implemented into the COMDES-MELT code to estimate the wall temperature minimum and maximum thresholds that support ice accretion, as observed by video confirmation. The results from this model spanned the range of wall temperatures measured on a previous engine that experienced ice accretion at certain operating conditions.

Description: This paper presents a new method for transonic pitching airfoils based on a RANS CFD study and the Theodorsen model of an oscillating pitching flat plate. This study quantifies the deviation of the lift coefficient predictions using CFD from that obtained using the Theodorsen model, which is based on the incompressible potential flow assumption. The present method corrects this theoretical model by modulating the Theodorsen functions by coefficient functions that depend on the reduced frequency and the Mach number. It is demonstrated that the modified theoretical model predicts lift coefficient in good agreement with the CFD results in the Mach number range from incompressible (M =0.2) to transonic (M =0.755) flow for a range of reduced frequencies typical of transonic flutter. The simulations are first validated by comparing pitching NACA0012 airfoil results with experimental results at transonic flight conditions, which establishes the requirements for a grid converged unsteady transonic solution. The hysteresis loop, Cl versus , attains a grid independent solution that compares well with experiment. The present correction method will guide the development of a new state space model for the Variable Camber Continuous Trailing Edge Flap (VCCTEF) system and eventually a new transfer function that will be incorporated in a new aeroelastic framework leading to an appropriate transonic flutter model for use in the future aircraft systems in development under the NASA Advanced Air Transportation Technologies (AATT) project.

Description: This PowerPoint presentation will discuss Aura's current spacecraft and OMI insturment status, highlight anyperformance trends and impacts to OMI operations, identify any operational changes and express concerns or potential process improvements. Reviewed by Eric Moyer, ESMO Deputy Project Manager.

Description: During Mars atmospheric entry, the Mars Science Laboratory (MSL) was protected by a 4.5 meters diameter ablative heatshield assembled in 113 tiles [1]. The heatshield was made of NASA's flagship ablative material, the Phenolic Impregnated Carbon Ablator (PICA) [2]. Prior work [3] compared the traditional one-dimensional and three-dimensional material response models at different locations in the heatshield. It was observed that the flow was basically one-dimensional in the nose and flank regions, but three-dimensional flow effects were observed in the outer flank. Additionally, the effects of tiled versus monolithic heatshield models were also investigated. It was observed that the 3D tiled and 3D monolithic configurations yielded relative differences for in-depth material temperature up to 18% and 28%, respectively, when compared to the a 1D model.

Description: No abstract available

Description: No abstract available

Description: A modified and extended version of a convergence test for wind tunnel strain-gage balance load iterations was implemented. The test uses an upper bound of the Lipschitz constant to assess convergence characteristics of balance load predictions if the Iterative Method is applied. Convergence is expected within the use envelope of the balance whenever this upper bound is less than the threshold of one. It is explained in great detail how the convergence test can be applied to the two load iteration equation types that are currently being used in the aerospace testing community. In addition, the application of the test to balances with bi-directional output characteristics is discussed. It is also shown how numerical differentiation can be used in order to obtain partial derivatives that are needed for the calculation of the Lipschitz constant. Finally, machine calibration data of NASA's MC60E six-component force balance is selected to demonstrate both implementation and use of the convergence test.

Description: This presentation includes the UAS-Enabled Market Categories used in Study, as well as the reason for the UAS-NAS NO Chase COA flight. It discusses the transitioning of a UA from different airspaces. UAS Integration is a community wide effort, and the FAA Symposium provides attendees with the opportunity to engage face-to-face with a cross-section of government and industry leaders and innovators about the latest industry developments, regulations, research, and other initiatives to safely integrate UAS into the National Airspace System (NAS).

Description: The design of a modular multi-physics high-order space-time finite-element framework is presented together with its extension to allow monolithic coupling of different physics. One of the main objectives of the framework is to perform efficient high- fidelity simulations of capsule/parachute systems. This problem requires simulating multiple physics including, but not limited to, the compressible Navier-Stokes equations, the dynamics of a moving body with mesh deformations and adaptation, the linear shell equations, non-re effective boundary conditions and wall modeling. The solver is based on high-order space-time - finite element methods. Continuous, discontinuous and C1-discontinuous Galerkin methods are implemented, allowing one to discretize various physical models. Tangent and adjoint sensitivity analysis are also targeted in order to conduct gradient-based optimization, error estimation, mesh adaptation, and flow control, adding another layer of complexity to the framework. The decisions made to tackle these challenges are presented. The discussion focuses first on the "single-physics" solver and later on its extension to the monolithic coupling of different physics. The implementation of different physics modules, relevant to the capsule/parachute system, are also presented. Finally, examples of coupled computations are presented, paving the way to the simulation of the full capsule/parachute system.

Description: This presentation will cover the structure of the unmanned aircraft systems (UAS) integration into the national airspace system (NAS) project (UAS-NAS Project). The talk also details the motivation of the project to help develop standards for a detect-and-avoid (DAA) system, which is required in order to comply with requirements in manned aviation to see-and-avoid other traffic so as to maintain well clear. The presentation covers accomplishments reached by the project in Phase 1 of the research, and touches on the work to be done in Phase 2. The discussion ends with examples of the display work developed as a result of the Phase 1 research.

Description: This is a pull-up banner of the Multifunctional Structures for High-Energy Lightweight Load-bearing Storage (M-SHELLS) technology that will be on display at the SciTech Conference in January 2018. Efforts in Multifunctional Structures for High Energy Load-Bearing Storage (M-Shells) are pushing the boundaries of development for hybrid electric propulsion for future commercial aeronautical transport. The M-Shells hybrid material would serve as the power/energy storage of the vehicle and provide structural integrity, freeing up usable volume and mass typically occupied by bulky batteries. The ultimate goal is to demonstrate a system-level mass savings with a multifunctional structure with energy storage.

Description: Performing impact risk assessment for the 2017 Planetary Defense Conference (PDC17) hypothetical impact exercise, to take place at the PDC17 conference, May 15-20, 2017. Impact scenarios and trajectories are developed and provided by NASA's Near Earth Objects Office at JPL (Paul Chodas). These results represent purely hypothetical impact scenarios, and do not reflect any known asteroid threat. Risk assessment was performed using the Probabilistic Asteroid Impact Risk (PAIR) model developed by the Asteroid Threat Assessment Project (ATAP) at NASA Ames Research Center. This presentation includes sample results that may be presented or used in discussions during the various stages of the impact exercisecenter dot Some cases represent alternate scenario options that may not be used during the actual impact exercise at the PDC17 conference. Updates to these initial assessments and/or additional scenario assessments may be performed throughout the impact exercise as different scenario options unfold.

Description: A study into the effects of altitude on an aircraft thermal Ice Protection System (IPS) performance has been conducted by the National Research Council Canada (NRC) in collaboration with the NASA Glenn Icing Branch. The study included tests of an airfoil model, with a heated-air IPS, installed in the NRCs Altitude Icing Wind Tunnel (AIWT) at altitude and ground level conditions.

Description: The NATO HFM-247 Working Group is creating a summary report of the group's activities on human-autonomy teaming. This chapter is a summary of our at NASA Ames work toward developing a framework for human-autonomy teaming (HAT) in aviation. The purpose of this project was to demonstrate and evaluate proposed tenets of HAT. The HAT features were derived from three tenets and were built into an automated recommender system on a ground station. These tenets include bi-directional communication, automation transparency, and operator directed interface. This study focused primarily on interactions with one piece of automation, the Autonomous Constrained Flight Planner (ACFP). The ACFP is designed to support rapid diversion decisions for commercial pilots in off-nominal situations. Much effort has gone into enhancing this tool not only in capability but also in transparency. In this study, participants used the ACFP at a ground station designed to aid dispatchers in a flight following role to reroute aircraft in situations such as inclement weather, system failures and medical emergencies. Participants performed this task both with HAT features enabled and without and provided feedback. We examined subjective and behavioral indicators of HAT collaborations using a proof-of-concept demonstration of HAT tenets. The data collected suggest potential advantages and disadvantages of HAT.

Description: A research team of U.S. Government agencies and engine manufacturers conducted an experiment to test volcanic-ash ingestion by a NASA owned engine in the same family as the PW 2000 that was donated by the U.S. Air Force. The experiment, called Vehicle Integrated Propulsions Research (VIPR) test, was conducted under the auspices of NASAs Convergent Aeronautics Solutions (CAS) Program and took place in summer of 2015 at Edwards AFB in California as an on-ground, on-wing test. The primary objectives of the volcanic ash test were to determine the effect on the engine of several hours of exposure to low to moderate ash concentrations and to evaluate the capability of engine health management technologies for detecting these effects. The target concentrations of volcanic ash tested were at 1 and 10 mgm3. A natural volcanic ash was used that is representative of distal ash clouds many 100s to 1000 km from a volcanic source. The glassy ash particles were expected to soften and become less viscous when exposed to the high temperatures of the combustion chamber, then stick to the nozzle guide vanes of the high-pressure turbine and this was observed. Numerous observations and measurements of the engines performance and degradation were made during the course of the experiment, including borescope inspections after each test run. The engine has been disassembled so that detailed inspections of the engine effects have been made. A summary of the test methodology and execution will be made along with results from the test. While not intended to be sufficient for rigorous certification of engine performance when ash is ingested, the experiment should provide useful information to aircraft manufacturers, airline operators, and military and civil regulators in their efforts to evaluate the range of risks that ash hazards pose to aviation.

Description: This paper presents a new method to design Robust Switching State-Feedback Gain-Scheduling (RSSFGS) controllers for Linear Parameter Varying (LPV) systems with uncertain scheduling parameters. The domain of scheduling parameters are divided into several overlapped subregions to undergo hysteresis switching among a family of simultaneously designed LPV controllers over the corresponding subregion with the guaranteed H-infinity performance. The synthesis conditions are given in terms of Parameterized Linear Matrix Inequalities that guarantee both stability and performance at each subregion and associated switching surfaces. The switching stability is ensured by descent parameter-dependent Lyapunov function on switching surfaces. By solving the optimization problem, RSSFGS controller can be obtained for each subregion. A numerical example is given to illustrate the effectiveness of the proposed approach over the non-switching controllers.

Description: Several multimodel ensemble methods are selected and further developed to improve the deterministic and probabilistic prediction skills of individual wake-vortex transport and decay models. The different multimodel ensemble methods are introduced, and their suitability for wake applications is demonstrated. The selected methods include direct ensemble averaging, Bayesian model averaging, and Monte Carlo simulation. The different methodologies are evaluated employing data from wake-vortex field measurement campaigns conducted in the United States and Germany.

Description: Human and robotic missions to Mercury and Saturn are presented and analyzed with a range of propulsion options. Historical studies of space exploration, in-situ resource utilization (ISRU), and industrialization all point to the vastness of natural resources in the solar system. Advanced propulsion benefitted from these resources in many ways. While advanced propulsion systems were proposed in these historical studies, further investigation of nuclear options using high power nuclear thermal and nuclear pulse propulsion as well as advanced chemical propulsion can significantly enhance these scenarios. Updated analyses based on these historical visions will be presented. Nuclear thermal propulsion and ISRU enhanced chemical propulsion landers are assessed for Mercury missions. At Saturn, nuclear pulse propulsion with alternate propellant feed systems and Titan exploration with chemical propulsion options are discussed. In-situ resource utilization was found to be critical in making Mercury missions more amenable for human visits. At Saturn, refueling using local atmospheric mining was found to be difficult to impractical, while refueling the Saturn missions from Uranus was more practical and less complex.

Description: This paper summarizes the development of lean direct injection (LDI) combustor technology at, or in collaboration with, the NASA Glenn Research Center. These configurations differ mainly in fuel-air mixing strategy. The paper reviews the NOx performance and operability characteristics of multiple LDI configurations tested at NASA Glenn.

Description: This paper summarizes the development of lean direct injection (LDI) combustor technology at, or in collaboration with, the NASA Glenn Research Center. These configurations differ mainly in fuel-air mixing strategy. The paper reviews the NOx performance and operability characteristics of multiple LDI configurations tested at NASA Glenn.

Description: Convection speeds of turbulent velocities in jets, including multi-stream jets with and without flight stream, were measured using an innovative application of time-resolved particle image velocimetry. The paper describes the unique instrumentation and data analysis that allows the measurement to be made. Extensive data is shown that relates convection speed, mean velocity, and turbulent velocities for multiple jet cases. These data support the overall observation that the local turbulent convection speed is roughly that of the local mean velocity, biased by the relative intensity of turbulence.

Description: This work continues the analysis of data obtained during a 2017 NASA DGEN Aeropropulsion Research Turbofan (DART) core/combustor-noise baseline test in the NASA GRC Aero-Acoustic Propulsion Laboratory (AAPL). The DART is a cost-efficient testbed for the study of core-noise physics and mitigation. Acoustic data were simultaneously acquired using the AAPL overhead microphone array in the engine aft-quadrant farfield, a single midfield microphone, and two infinite-tube-probe sensors for unsteady pressures at the core-nozzle exit. The data are here examined on an 1/3-octave basis as a first step in extending and improving core-noise prediction capability.

Description: Increasing demand for improved capabilities of small unmanned aircraft systems (sUAS) has generated interest in improving the design techniques for these vehicles. sUAS have typically been designed using iterative methods with multiple prototypes, but advancements in aircraft design software will make it possible to generate conceptual designs of very small VTOL aircraft with reduced hardware prototyping. This paper describes a research effort to generate a conceptual design of an approximately 6-lb quadcopter using the NASA rotorcraft design software NDARC. Wind tunnel and hover test data are used to validate and refine the conceptual design results. The effects of parametric design variations on vehicle scale are shown. The design study described herein shows that the NDARC software, which was designed for full-scale rotorcraft, can be used to design and evaluate sUAS vehicles.

Description: This paper adds data to help develop simulator motion guidelines for stall recovery training by identifying time-varying manual control behavior in a stall recovery task under different simulator motion conditions. A study was conducted in the NASA Ames Vertical Motion Simulator, where seventeen general aviation pilots performed a stall recovery task. Pilots had to follow a flight director through four stages of the stall recovery task. A time-varying identification method was used to quantify how pilots weigh position and velocity information throughout different stages of the task, in both roll and pitch. Four motion configurations were used: no motion, generic hexapod motion, enhanced hexapod motion and full motion. Pilot performance was highest for the enhanced hexapod and full motion conditions in both roll and pitch, and the lowest for the condition with no motion. The time-varying identification method revealed that, in the roll axis, pilot position gain did not significantly change between time segments, but was the lowest for the condition with no motion. The pilot velocity gain was significantly different between motion conditions, the largest difference being found at the beginning of the stall. The enhanced hexapod motion condition had the highest pilot velocity gain. In the pitch axis, the pilot position gain was significantly different between time segments but not between motion conditions. The pitch pilot velocity gain was highest for the full motion condition and increased at the beginning of the stall, but did not change significantly for the other motion conditions. Overall, pilot control behavior under enhanced hexapod motion was more similar to that under full aircraft motion compared to standard hexapod motion. This indicates that motion cueing on hexapod simulators might be improved for stall recovery training by using the enhanced hexapod motion developed in previous experiments.

Description: The Elytron 2S is a prototype aircraft concept to allow VTOL capabilities together with fixed wing aircraft performance. It has a box wing design with a centrally mounted tilt-wing supporting two rotors. This paper explores the aerodynamic characteristics of the aircraft using computational fluid dynamics in hover and low speed forward flight, as well as analyzing the unique control system in place for hover. The results are then used to build an input set for NASA Design and Analysis if Rotorcraft software allowing trim and flight stability and control estimations to be made with SIMPLIFLYD.

Description: NASA funded the preliminary design of a flight demonstrator aircraft with a greatly reduced sonic boom signature to enable supersonic flight over land. In 2017, two tests were performed at the NASA Glenn Research Center 8- by 6-foot Supersonic Wind Tunnel, an aerodynamic stability/control test and an inlet performance test. The inlet was unique due to the location on the vehicle, located on the top centerline near the rear of the aircraft. Test data provided a validation and performance dataset for engine integration on the demonstrator vehicle. The subject of this report is the subsonic and supersonic performance data collected for the centerline top-mounted inlet.

Description: Tones were encountered in large-scale, multi-stream nozzle tests in the Aeoacoustics Propulsion Laboratory (AAPL). A different coaxial nozzle used in a past experiment also produced tones. In this paper, we present experimental and COMSOL results addressing the tone mechanism in the latter nozzle.

Description: A study has been performed to determine best practices for generating unstructured grids for Reynolds-Averaged Navier-Stokes (RANS) simulations of jet flows. The Axisymmetric Near-Sonic Jet Case from the Turbulence Modeling Resource was used for this study: a Mach 0.985 flow through the 2-in. diameter Acoustic Reference Nozzle (ARN2). Simulations were run with FUN3D and used the Menter Shear Stress Transport (SST-V), Spalart-Allmaras (S-A), and k-kL turbulence models. The axial velocity and turbulent kinetic energy fields in the jet plume of the unstructured grid solutions were compared to those of the baseline structured grid solution provided by the Turbulence Modeling Resource. Only solutions using grids with structured-like elements in the jet plume showed good agreement with the baseline structured grid solution. Using the SST-V turbulence model, the fully unstructured grid solutions predicted the jet potential core to decay upstream of the baseline solution. With the S-A turbulence model, the unstructured grid solutions predicted the jet potential core to decay upstream of the baseline solution. The solutions using the k-kL turbulence model seemed less sensitive to grid topology. Nozzle massflow and thrust performance were also compared for all simulations. Based on the results of this study, it is currently recommended that structured-like grid elements are used in the plumes of jet flows; unstructured grid elements can be used elsewhere.

Description: The formation of ice over lifting surfaces can affect aerodynamic performance. The ability to predict ice accumulation and the resulting degradation in vehicle performance is essential to determine the limitations of aircraft in icing encounters. The consequences of underestimating performance degradation can be serious and so it is important to produce accurate predictions, particularly for severe icing conditions. The simulation of ice accretion is a challenging multidisciplinary problem that requires close collaboration between the computational and ground test communities. This paper describes three recent case studies and the lessons learned through collaborative experiments and computations in aircraft icing- one for large commercial transports, one for rotorcraft, and one dealing with icing on regional jets.