ALBERT

All Library Books, journals and Electronic Records Telegrafenberg

X
feed icon rss

Your email was sent successfully. Check your inbox.

An error occurred while sending the email. Please try again.

Proceed reservation?

Export
Filter
  • Aircraft Design, Testing and Performance  (111)
  • Aircraft Stability and Control  (52)
  • Temperatur  (36)
  • 1950-1954  (126)
  • 1940-1944  (73)
Collection
Keywords
Years
Year
  • 1
    facet.materialart.
    Unknown
    Das Frühjahr 1952 und die Frostschäden im Niederelbegebiet (1952)
    In:  Mitt. Obstbauvers. ring Altes Land, York 7:102-115.
    Details
    Publication Date: 1952
    Description: Bericht über die Folgen des Spätfrostes im Jahr 1952 an verschiedenen Obstbaumarten (Äpfel, Birnen, Kirschen, Beeren) KATASTER-BESCHREIBUNG: Einfluss der Witterung (Temperatur, Niederschlag) auf den Ertrag von Obstbäumen. KATASTER-DETAIL: Delta T (Januar, Februar, März) +, dann Vegetationsbeginn - (früher); Delta Nied (Februar-Mai) -, dann Ertrag (Boskoop, Coulon, Kehdinger Rambur, Cox) -; Delta T (Mai) - : T 〈 0 °C(Spätfröste), dann Schäden der Früchte an Obstbäumen -;
    Keywords: Niederelbe ; 1952 ; Apfel ; Kirsche ; Boden ; Ertrag ; Niederschlag ; Temperatur ; Witterung ; Frost ; Obst ; Birne
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 2
    facet.materialart.
    Unknown
    Über den Einfluß von Temperatur und Futterpflanze auf die Entwicklung von Hyphantria cunea (1953)
    In:  Nachrichtenblatt des deutschen Pflanzenschutzdienstes 5, Nr.10; p.145-150
    Details
    Publication Date: 1953
    Description: Der Autor untersuchte die für das Auftreten des weißen Bärenspinners günstigen Temperaturen im ehemaligen Jugoslawien (Palic, Vojvodina) und Österreich (Burgenland) und identifizierte die Temperaturen von Mai bis August als wichtige Einflußfaktoren auf die Entwicklungszeit des Falters. Hierdurch konnten Temperaturen identifiziert werden bei denen eine, zwei oder sogar drei Generationen im Jahresverlauf vorkommen können. Sobald die Temperaturen 14-15°C überschreiten, kann die Entwicklung der ersten Generation beginnen. Die gewonnenen Erkenntnisse wurden dazu eingesetzt, um das Ausbreitungspotential des Schmetterlings aufgrund klimatischer Parameter nach Mitteleuropa abzuschätzen. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Jugoslawien, Österreich, Deutschland ; 1946-1952 ; Pflanzenschädling ; Temperatur
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 3
    facet.materialart.
    Unknown
    Über das Massenauftreten des Apfelwicklers (Obstmade) im Jahre 1950 in Bayern (1951)
    In:  Ratgeber Obst-, Gartenbau, Geflügelzucht, Heft 5, p. 102-103
    Details
    Publication Date: 1951
    Description: Beschreibung der Faktoren für Lebenslauf und Massenvermehrung sowie Ratschläge zur Bekämpfung des Apfelwicklers mittels Spritzungen KATASTER-BESCHREIBUNG: Zusammenhang zwischen Entwicklung des Apfelwicklers in seinen Stadien und der Temperatur sowie der Feuchtigkeit KATASTER-DETAIL: Delta T: Tmin 〈 10°C, dann keine Entwicklung von Ei und Raupe möglich; T 〈 11°C, dann keine Entwicklung von Puppe möglich; Delta T +, dann Einbohren in den Apfel +; T〈15°C, dann kein Einbohren möglich; Tmit(Dekade)〉15°C, dann Flugbeginn; Delta Nied (Mai+Juni)-, dann Apfelwickler +
    Keywords: Bayern ; 1950 ; Pflanzenschädling ; Temperatur ; Obst
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 4
    facet.materialart.
    Unknown
    Untersuchungen zur Bekämpfung der Rapsschädlinge. III. Zur Biologie und Bekämpfung des Kohlschotenrüßlers (Ceutorrhynchus assimilis Payk.) und der Kohlschotengallmücke (Dasyneura brassicae Winn.) (1954)
    In:  Nachrichtenblatt deutsch. Pflanzenschutzdienst, p. 128-135
    Details
    Publication Date: 1954
    Description: Bericht über Untersuchungen zur Terminwahl für die Bekämpfung von Kohlschotenrüßler und Kohlschotengallmücke sowie Vergleiche der Ergebnisse mit der bisherigen Literatur KATASTER-BESCHREIBUNG: Einfluss der Temperatur auf das Auftreten des Kohlschotenrüßlers KATASTER-DETAIL: Delta T +: Tmit 〉 15°C, dann Erscheinen des Kohlschotenrüßlers
    Keywords: Sachsen-Anhalt ; 1952-1953 ; Pflanzenschädling ; Temperatur ; Raps
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 5
    facet.materialart.
    Unknown
    Die Beziehungen zwischen dem Lebensraum und Lebensäußerungen von Insekten (1944)
    In:  Anz. Schädl.kunde 20: 16ff
    Details
    Publication Date: 1944
    Description: Beziehung zwischen Klima und Insektenbiologie KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland, teilw. einzelne Regionen ; 1936-1941 ; Insekten ; Luftfeuchte ; Forst ; Klima ; Niederschlag ; Pflanzenschädling ; Temperatur
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 6
    facet.materialart.
    Unknown
    Über die Wirkung des Rapserdfloh-Larvenbefalls auf die Rapspflanze (1950)
    In:  Mitteilungen aus der Biologischen Zentralanstalt für Land- und Forstwirtschaft, Berlin-Dahlem, Heft 69
    Details
    Publication Date: 1950
    Description: Bericht über die Ergebnisse der Untersuchungen zu den Wechselwirkungen zwischen Larve und Wirtspflanze KATASTER-BESCHREIBUNG: Einfluss der Temperatur auf den Larvenbefall KATASTER-DETAIL: Delta T -, dann Entwicklungsdauer der Larven +; T 〉 0°C, dann Froststarre und Wanderfähigkeit -; Delta T - und Delta Relf +, dann Larvenmortalität +
    Keywords: Berlin-Dahlem ; 1948-1949 ; Insekten ; Luftfeuchte ; Pflanzenschädling ; Temperatur ; Raps
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 7
    facet.materialart.
    Unknown
    Zur Biologie von Dendrolimus pini L. (Lep., Lasiocampidae) (1944)
    In:  Ann. ent. fenn. 10: 181-183
    Details
    Publication Date: 1944
    Description: Beschreibung des Überwinterungsverhaltens des Kiefernspinners KATASTER-BESCHREIBUNG: Zusammenhang zwischen geografischer Breite, Temperatur und dem Überwinterungsverhalten des Kiefernspinners KATASTER-DETAIL: Delta T-, dann zweimaliges Überwintern der Larven bei Versuchen in Finnland
    Keywords: Finnland ; 1940-44 ; Insekten ; Kiefer ; Pflanzenschädling ; Temperatur
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 8
    facet.materialart.
    Unknown
    Der Zusammenbruch einer Massenvermehrung von Diprion pini L. und seine Ursachen (1942)
    In:  Ztschr. angew. Ent. 29: 367-411
    Details
    Publication Date: 1942
    Description: Untersuchungen zu biotischen und abiotischen Ursachen für den Zusammenbruch der Population der Kiefernbuschhornblattwespe KATASTER-BESCHREIBUNG: Ursachen für den Zusammenbruch der Kiefernbuschhornblattwespen-Population neben dem harten Winter 1939/40 eine andauernde Schönwetterperiode Ende April/Anfang Mai und vor allem stärkere Vermehrung der Feinde KATASTER-DETAIL: Delta sonn +, (April-Mai) führte zu erhöhten Vertrocknen der Kokons der Kiefernbuschhornblattwespe im Jahr 1940
    Keywords: Nordostdeutschland ; 1939-40 ; Kiefer ; Pflanzenschädling ; Temperatur ; Sonnenscheindauer
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 9
    facet.materialart.
    Unknown
    Die Übervermehrung von Diprion pini L. im westslowakischen Kieferngebiet (1941)
    In:  Ztschr. Pfl.krankh. 51: 257-278
    Details
    Publication Date: 1941
    Description: Beschreibung der Massenvermehrung der Kiefernblattwespe, Hauptgrung ist die Umwandlung von ursprünglich Laubwaldgesellschaften in reine Kieferngesellschaften, Bedeutung der Temperatur für das Überliegen der Larven KATASTER-BESCHREIBUNG: Temperatur und Luftfeuchte für das Überliegen der Larven entscheidend und damit auch für ein Massenauftreten im darauffolgenden Jahr, Begünstigung der Parasitierung der Kieferblattwespe KATASTER-DETAIL: Delta T- (Juli-August und im Winter), dann Geschlechterfolge von Diprion pini stark dezimiert
    Keywords: Slowakei ; 1939-40 ; Insekten ; Luftfeuchte ; Kiefer ; Pflanzenschädling ; Temperatur ; Parasit
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 10
    facet.materialart.
    Unknown
    Untersuchungen über Buschhornblattwespen (Diprion) (1942)
    In:  Ztschr. angew. Ent. 29: 412-441 u. 601-635
    Details
    Publication Date: 1942
    Description: Beschreibung der Biologie der Buschhornblattwespe vom Schlüpfen, über die Entwicklung bis hin zum Überliegen und die abiotischen Sterlichkeitsursachen, u.a. witterungsbedingt KATASTER-BESCHREIBUNG: Beginn der Frühjahrsgeneration ist klima- und wetterbedingt, unter günstigen Bedingungen (milder Winter) bereits im Januar Beginn der Entwicklung und Schlupfbeginn ab Anfang April KATASTER-DETAIL: Tmit- (Spätfrühjahr und Frühwinterwitterung) , dann Schlupfbeginn später und Anteil der Überlieger höher
    Keywords: Mecklenburg-Vorpommern ; 1937-1940 ; Insekten ; Kiefer ; Pflanzenschädling ; Temperatur ; Vegetationsperiode ; Wachstum ; Witterung
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 11
    facet.materialart.
    Unknown
    Massenvermehrung forstlicher Schadinsekten (1941)
    In:  Dtsch. Forstztg. 10: 307-308
    Details
    Publication Date: 1941
    Description: Beschreibung der großen Frassschäden der letzten Jahrzehnte, bezug der Temperatur und des Niederschlages auf die Entwicklungsmöglichkeit einer Population KATASTER-BESCHREIBUNG: Ziiterte Untersuchungen zur Entwicklung der Nonnenraupe KATASTER-DETAIL: Delta T+ (Temperaturoptimum von 21.5°C, Ende April-Anfang Mai), dann günstige Entwiclungsbedingungen Delta Nied- (relative Feuchte schwankt zwischen 50-100%), dann Absterben großer Zahl futtersuchender Raupen
    Keywords: Deutschland, teilw. einzelne Regionen ; 1850-1940 ; Insekten ; Luftfeuchte ; Fichte ; Forst ; Kiefer ; Niederschlag ; Pflanzenschädling ; Temperatur
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 12
    facet.materialart.
    Unknown
    Bioclimatic study of the European spruce sawfly in Quebec [Gilpinia hercyniae] (1943)
    In:  Rev. canad. Biol. 2: 149-167
    Details
    Publication Date: 1943
    Description: Studien über die Schlupftermine der Europäischen Fichtenbuschhornblattwespe, Übertragbarkeit von Entwicklungstadien bei gleicher klimatischen Bedingungen KATASTER-BESCHREIBUNG: Durch Einteilung in klimatische Zonen konnte die Unterschiede in Tagen des Ausschlüpfen aus den Eiern der Fichtenbuschhornblattwespe für Kanada und die USA dargestellt werden. KATASTER-DETAIL:
    Keywords: Kanada und USA ; 1940-42 ; Insekten ; Fichte ; Pflanzenschädling ; Temperatur
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 13
    facet.materialart.
    Unknown
    Einflüsse abiotischer Umweltsfaktoren auf den Schwammspinner (Lymantria dispar L.) im Eistadium während der Winterdiapause. 1. Wirkung des Eises (1943)
    In:  Ztschr. ges. Forstwes. 75 (69): 105-132
    Details
    Publication Date: 1943
    Description: Untersuchungen über die Wirkung von Schnee, Eis und Kälte auf die Eigelege des Schwammspinners KATASTER-BESCHREIBUNG: Niedrige Temperaturen (Januar-März) von bis zu -11.4°C hatte keine nachhaltige Auswirkungen auf die Vitalität der Eigelege, eher waren mechanische Beschädigungen z.B. durch Abkratzen der Eigelege Ursachen für das Nichtschlüpfen der Tiere KATASTER-DETAIL:
    Keywords: Kroatien, Europa ; 1938-40 ; Insekten ; Eiche ; Pflanzenschädling ; Temperatur ; Frost
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 14
    facet.materialart.
    Unknown
    Witterung und Obstertrag (1943)
    In:  Gartenbauwissenschaft Bd. 17, S.603-615
    Details
    Publication Date: 1943
    Description: Einfluss der Temperatur und des Niederschlages auf den Ernteertrag von Birnen und Äpfeln KATASTER-BESCHREIBUNG: Durch Berechnung von Kennziffern zu Wirkung des Sommerregens auf den Obstertrag wird die Bedeutung der Niederschläge in bestimmten Monaten des Vor- und des Erntejahres bestimmt KATASTER-DETAIL: Nied+(Oktober des Vorjahres) und Nied+ (Juli des Erntejahres), dann hohe Erträge von Äpfeln und Birnen
    Keywords: Holstein ; 1916-1935 und 1921-1941 ; Apfel ; Ertrag ; Korrelationsmethode ; Niederschlag ; Rangordnungsmethode ; Temperatur ; Birne
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 15
    facet.materialart.
    Unknown
    Die Beziehung zwischen Ertrag und Witterung beim Kernobst (1952)
    In:  Z. f. Acker- und Pflanzenbau 95:233-260
    Details
    Publication Date: 1952
    Description: Zusammenhang zwischen der Temperatur und dem Niederschlag zu unterschiedlichen Zeitpunkten KATASTER-BESCHREIBUNG: (Einteilung in Dekaden) zu verschiedenen, ertragsrelevanten Zeiträumen (Blühreife, Anlagestadium, Knospenstadium und Blütenstadium) von Apfel und Birnen und Zusammenhang zu Niederschlag und Temperatur bei verschiedenen Sorten KATASTER-DETAIL: Nied+(〉30mm) (Knospendifferenzierung, 20.6-20.7. des Vorjahres), Nied+(〉70mm im März), Nied+ (〉20mm 1-10 Tage vor der Blüte), Tmit*(Tmin 〈-2°C als Nachftrost kritisch, vor, währed und 30 Tage nach der Blüte) und Nied- (〈70mm, bis 30 Tage nach der Blüte) führten zu hohen Erträgen
    Keywords: Baden-Württemberg, Hohenheim ; 1936-1947 ; Apfel ; Ertrag ; Korrelationsmethode ; Niederschlag ; Temperatur ; Witterung ; Frost ; Obst ; Birne
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 16
    facet.materialart.
    Unknown
    Zusammenhänge zwischen Jahreswitterung, Düngung und Erträgen im Dikopshofer Dauerversuch (1942)
    In:  Landwirtschaftl. Jahrbuch 68:642-686
    Details
    Publication Date: 1942
    Description: Ableitung kritischer Faktoren (Temperaturoptima und Wasserversorgung) in einzelnen Wachstumsstadien KATASTER-BESCHREIBUNG: Zusammenhang zwischen Temperaturänderung während der Blüte von Weizen und dem Ertrag KATASTER-DETAIL: Delta T + und -: Tmit von 14-15°C, Änderung um +1 K auf 16°C, aber auch Rückgang um 2K auf 13°C, dann Rückgang des Ertrages
    Keywords: Kölner Bucht ; 1907-37 ; Boden ; Ertrag ; Korrelationsmethode ; Niederschlag ; Roggen ; Temperatur ; Weizen ; Witterung ; Düngung ; Hackfrüchte
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 17
    facet.materialart.
    Unknown
    Landwirtschaftlich beachtliche Windwirkung und Windschutz in der Landwirtschaft. (1943)
    In:  Kulturtechniker, Berlin 46:19-41.
    Details
    Publication Date: 1943
    Description: Bedeutung und Wirkung des Windschutzes auf Anbauart, Fruchtfolge, Gare- und Bodenpflege, Schlageinteilung, Verdunstung, Deck-, Schutz-, Mischfrucht- und Streifenanbau KATASTER-BESCHREIBUNG: Einfluss von Windschutz auf den Ertrag KATASTER-DETAIL: Windschutz +, dann Delta T(Tag) + und Delta T(Nacht)-; Windschutz +, dann Delta Relf +; Windschutz +, dann Verdunstung -; Windschutz +, dann Bodenerosion -; Windschutz +, dann Schneeanhäufung +; angepasste Bodenbearbeitung (schollige, klumpige Bodenoberfläche), dann Wasserhaltungsfähigkeit + -〉 Windschutz +, dann Ertragserhöhung + bzw. ++ (3-400%; ++: Körnerfrüchte auf 20-25vH, Rüben, Gräser, Leguminosen; +: Sommergetreide, Hafer )
    Keywords: weltweit ; letzten100 Jahre ; Boden ; Ertrag ; Niederschlag ; Temperatur ; Verdunstung ; Wind ; Frost
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 18
    facet.materialart.
    Unknown
    Inwieweit berücksichtigt der Landwirt den Klimafaktor? (1940)
    In:  Landw. Jahrbuch 89:793-808.
    Details
    Publication Date: 1940
    Description: Allgemeiner Bericht über Anpassungen der Landwirtschaft an das Klima, wie beispielsweise extensive und intensive Landwirtschaft, Fruchtfolge, Bodenbearbeitung, Frostschadenverhütung und Düngung. KATASTER-BESCHREIBUNG: - KATASTER-DETAIL: -
    Keywords: Deutschland ; 1. Hälfte 20. Jahrhundert ; Anbautermine ; Boden ; Landwirtschaft ; Niederschlag ; Temperatur ; Verdunstung ; Wassermangel ; Düngung ; Frost ; Sonnenscheindauer
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 19
    facet.materialart.
    Unknown
    Untersuchungen zur anholozyklischen Überwinterung der grünen Pfirsichblattlaus (Myzodes persicae Sulz.) an Brassicaceen (1952)
    In:  Mitteilungen aus der Biologischen Zentralanstalt für Land- und Forstwirtschaft Berlin-Dahlem, Heft 73
    Details
    Publication Date: 1952
    Description: 4-jährige Feldexperimente und -beobachtungen zum winterlichen Massenwechsel der grünen Pfirsichblattlaus KATASTER-BESCHREIBUNG: Entscheidende Faktoren für Vorkommen und Ausmaß der anholozyklischen Überwinterung KATASTER-DETAIL: Delta T-: T(Bodennähe)〈= -5°C, dann Myzodes persicae -; Winterfröste: Dauer + , zeitiger, Minimum -, dann Myzodes persicae -; Nachwinter: Delta T + und Delta Nied -, dann Myzodes persicae +
    Keywords: Kölner Bucht ; 1948 - 1951 ; Pflanzenschädling ; Temperatur
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 20
    facet.materialart.
    Unknown
    Beiträge zur Epidemiologie und Prognose des Rapserdflohs (Psylloides crysocephala L.) (1953)
    In:  Beiträge zur Entomologie, Band 3, p. 518-529
    Details
    Publication Date: 1953
    Description: Untersuchungen zum Ausbleiben des erwarteten starken Befalls im Herbst 1952 und Vergleich mit bereits veröffentlichten Erkenntnissen zum Massenwechsel des Rapserdflohs; KATASTER-BESCHREIBUNG: Abhängigkeit des Massenwechsels des Rapserdflohs von der Witterung (Temperatur) KATASTER-DETAIL: Delta T -: Delta T (August, September) -, dann Zuwanderung der Rapserdflöhe -;
    Keywords: Sachsen-Anhalt ; 1951-1953 ; Pflanzenschädling ; Temperatur ; Witterung ; Raps
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 21
    facet.materialart.
    Unknown
    Klima und Witterung in ihrer Auswirkung auf die Qualität pflanzlicher Erzeugnisse (1952)
    In:  Landw. Forsch. Darmstadt, 2. Sonderheft: 51-60
    Details
    Publication Date: 1952
    Description: Überblick über die Zusammenhänge zwischen Klima bzw. Witterung und Pflanzenqualität von Ackerfrüchten, Wiesengräsern, Obst, Gemüse, Gewürzpflanzen und Wein KATASTER-BESCHREIBUNG: Einfluss der Witterung (Temperatur, Niederschlag, Sonnenschein, Strahlung) auf die Qualität verschiedener Anbaukulturen KATASTER-DETAIL: Delta T (Erntezeit) + und Delta Nied (Erntezeit) -, dann Feuchtigkeitsgehalt der Körner (Ackerfrüchte) -; Delta T (Erntezeit) - und Delta Nied (Erntezeit) +, dann Feuchtigkeitsgehalt der Körner (Ackerfrüchte) +; Delta T (Zeit der Kornausbildung) ++ und Delta Nied (Zeit der Kornausbildung) -, dann Stärkegehalt der Körner (Ackerfrüchte) - und Einweißgehalt der Körner + sowie Größe der Körner -; Delta T (Zeit von Milch- zur Voll- und Todreife) + und Delta Sonn (Zeit von Milch- zur Voll- und Todreife) + und Delta Nied (Zeit von Milch- zur Voll- und Todreife) -, dann besserer Kleber und gute Backfähigkeit; Delta blaue Strahlung +, dann Einweißgehalt - und Kleberqualität +; Delta Nied (Juni, Juli) +, dann Fermenttätigkeit +; Informationen zu den anderen Anbaukulturen: siehe Artikel
    Keywords: Deutschland ; 1. Hälfte 20. Jahrhundert ; Ertrag ; Getreide ; Niederschlag ; Temperatur ; Trockenheit ; Wachstum ; Witterung ; Hackfrüchte ; Obst ; Sonnenscheindauer ; Wein ; Gemüse
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 22
    facet.materialart.
    Unknown
    Klimaschäden. Betriebswirtschaftliche Betrachtungen aus dem mitteldeutschen Raum (1953)
    In:  Gesunde Pflanzen 5: 261-263
    Details
    Publication Date: 1953
    Description: Beschreibung der Auswirkungen von Spätfrösten auf den Ertrag von verschiedenen frostempfindlichen Kulturpflanzen (Winter-Gerste, Erbsen, Kartoffeln) KATASTER-BESCHREIBUNG: Einfluss der Witterung (Temperatur, Niederschlag) auf den Ertrag KATASTER-DETAIL: Delta T (April) + und Delta T (Mai) - (Spätfröste), dann Ertrag (Erbsen) --; Delta T (April) + und Delta T (Mai) - (Spätfröste), dann Erntezeitpunkt (Kartoffeln) + (später);
    Keywords: Mitteldeutschland ; 1952 ; Kartoffeln ; Anbautermine ; Boden ; Ertrag ; Niederschlag ; Temperatur ; Wachstum ; Wassermangel ; Witterung ; Frost ; Gerste ; Erbsen
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 23
    facet.materialart.
    Unknown
    Witterung und Pflanzenwachstum (unter Benutzung langjähriger phänologischer Beobachtungen aus Thüringen). (1952)
    In:  Akademie-Verlag Berlin, Abhandlungen des meteorologischen und hydrologischen Dienstes der deutschen demokratischen Republik, Nr. 14, Bd. II.
    Details
    Publication Date: 1952
    Description: Phänogramme und Beschreibung der Abhängigkeit verschiedenster Zeigerpflanzen des Frühlings (Schneeglöckchen, Rosskastanie, Flieder), des Sommers (Holunder, Roggen) und des Herbstes von meteorologischen Faktoren und Vergleich mit landwirtschaftlich wichtigen phänologischen Phasen KATASTER-BESCHREIBUNG: Eintritt phänologischer Phasen ist von den Temperatursummen abhängig; Einfluss der Temperatur auf den Ertrag KATASTER-DETAIL: Delta T +: T 〉 8°C, dann Beginn Pflanzenwachstum; Delta T (Mai und Juni) -, dann Erträge Winterroggen +;
    Keywords: Thüringen ; 1881-1909, 1929-1948 ; Getreide ; Landwirtschaft ; Niederschlag ; Phänologie ; Temperatur
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 24
    facet.materialart.
    Unknown
    Frühjahrstemperaturen und Apfelblütenstecherbekämpfung (1951)
    In:  Neue Mitt. Landwirtsch. 6, Nr.9; p.139-140
    Details
    Publication Date: 1951
    Description: Der Autor entwickelt ein Temperatursummenmodell zur Vorhersage der Kopula des Apfelblütenstechers. KATASTER-BESCHREIBUNG: Temperatursummenmodell zur Vorhersage der Kopula des Apfelblütenstechers KATASTER-DETAIL: Kopula tritt ab einer Temperatursumme (aufsummierte Stundenwerte) von 900-1000°C bei einer Basis von 8°C auf.
    Keywords: Hessen, Dippelshof ; 1948-1950 ; Apfel ; Pflanzenschädling ; Temperatur
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 25
    facet.materialart.
    Unknown
    Über die Frühjahrsentwicklung der grünen Pfirsichblattlaus (Myzodes persicae Sulzer) am Primärwirt im Hinblick auf ihre Bedeutung als Virusüberträger im Kartoffelfeld (1950)
    In:  Z. Pflanzenkrankheiten (Pflanzenpathol.) Pflanzenschutz, p. 351-357
    Details
    Publication Date: 1950
    Description: Untersuchungen zur Schlüpfzeit, der Generationszahl und der Abflugzeiten von Myzodes persicae Sulzer am Pfirsichbaum KATASTER-BESCHREIBUNG: Zusammenhang zwischen Klima, Witterung und Schlüpfablauf von Myzodes persicae KATASTER-DETAIL: Delta T -, dann Verzögerung im Schlüpfablauf
    Keywords: Bonn ; 1947-1950 ; Kartoffeln ; Pflanzenschädling ; Temperatur
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 26
    facet.materialart.
    Unknown
    Was wissen wir von der Blattfleckenkrankheit der Rübe (Cercospora beticola Sacc.) (1951)
    In:  Neue Mitt. Landwirtsch., p. 395-396
    Details
    Publication Date: 1951
    Description: Verbale Beschreibung des bisherigen Wissens über die Blattfleckenkrankheit und deren Erreger KATASTER-BESCHREIBUNG: Zusammenhang zwischen Witterung (Temperatur, Luftfeuchte) und dem Auftreten der Krankheit KATASTER-DETAIL: Delta T (Sommer) + und Delta Nied (Sommer) +, dann Auftreten von Cercospora +; Delta Relf +, dann Anzahl und Größe der Konidien +; Relf 〉 98%, dann Keimung der Konidien; Delta T: 20°C 〈 T 〈 30°C, dann schnellste Keimung der Konidien; 25°C 〈 T 〈 30°C, dann optimales Wachstum des Myzels; °C 〉 T 〈 40°C, dann kein Wachstum des Myzels
    Keywords: Deutschland ; 1950 ; Zuckerrüben ; Pflanzenkrankheit ; Temperatur ; Witterung
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 27
    facet.materialart.
    Unknown
    Witterungsfaktoren als Urheber der Massenvermehrung des Rübenderbrüßlers (Bothynoderes punctioventris) 1947-1949 in Mitteldeutschland (1951)
    In:  Zeitschrift für angewandte Entomologie, p.567-575
    Details
    Publication Date: 1951
    Description: Beobachtungen zum Massenauftreten des Rübenderbrüßlers in Abhängigkeit von der vorherrschenden Witterung KATASTER-BESCHREIBUNG: Zusammenhang zwischen der Witterung (Bodentemperatur und Bodenfeuchte) und dem Massenauftreten des Käfers KATASTER-DETAIL: Delta Nied (Sommer) +, dann Mortalität +; Delta T (Sommer des Vorjahres) + und Delta Nied (Sommer des Vorjahres) - sowie Delta T ( Frühjahr des Schadjahres) +, dann Massenauftreten des Käfers +; Delta T: Tmit (Boden) 〉 10°C, Auskriechen der Käfer aus dem Boden
    Keywords: Mitteldeutschland ; 1947-1949 ; Insekten ; Zuckerrüben ; Boden ; Landwirtschaft ; Niederschlag ; Pflanzenschädling ; Temperatur ; Trockenheit ; Witterung
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 28
    facet.materialart.
    Unknown
    Biologie, Epidemiologie und Bekämpfung des Rübenderbrüßlers (Bothynoderes punctiventris Germ.) (1952)
    In:  Beiträge zur Entomologie, Band 2, Nr. 2/3, p. 256-315
    Details
    Publication Date: 1952
    Description: Beobachtungen und Untersuchungen zur Biologie, Epidemiologie und Bekämpfung des Rübenderbrüßlers KATASTER-BESCHREIBUNG: Einflüsse der Witterung auf die Entwicklung und das Massenauftreten des Käfers KATASTER-DETAIL: Delta T und Delta Nied und Delta Sonn: T(Boden)〉8°C und Delta Nied -, Delta T (Luft) + und Delta Sonn +, dann Verlassen des Bodens; Delta T -, dann Unterbrechungen der Abwanderung +; Delta T und Delta Sonn: T〉=22°C und Sonnenschein, dann Flug; Delta T: T〉= 15-17°C, dann Reifung; T=26,2°C und Relf=30-37%, dann maximale Eizahl; T〈2°C, dann Erstarrungszustand; Delta Nied (Mai, Juni) -, dann Massenauftreten +; Delta T +, dann Eizahl +;
    Keywords: Sachsen-Anhalt ; 1950 ; Zuckerrüben ; Boden ; Niederschlag ; Pflanzenschädling ; Temperatur ; Witterung ; Sonnenscheindauer
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 29
    facet.materialart.
    Unknown
    Die Vergilbungskrankheit der Rübe (1954)
    In:  Mitteilungen aus der Biologischen Zentralanstalt für Land- und Forstwirtschaft Berlin-Dahlem, Heft 79
    Details
    Publication Date: 1954
    Description: Zusammenfassender Bericht über die in den Jahren 1947-1952 in Westdeutschland durchgeführten Untersuchungen zur Epidemiologie, Verbreitung, wirtschaftlichen Bedeutung und Bekämpfung dieser Virose KATASTER-BESCHREIBUNG: Hauptbefallsgebiete sind solche, mit mildem Winterklima, in denen die langjährigen Mittelwerte des kältesten Monats Januar nicht unter 0°C abfallen; KATASTER-DETAIL: Delta T(Sommer)+ und Delta Nied (Sommer) -, dann Delta t(Individualentwicklung der Überträger)- und Massenentwicklung (der Überträger) +; Delta T(Sommer)+ und Delta Nied (Sommer)-, dann Vergilbungsschäden +; Delta T - und Delta Lichtintensität -, dann Wirkung des Virus -;
    Keywords: Westdeutschland ; 1947-1952 ; Infektionskrankheiten ; Ertrag ; Niederschlag ; Pflanzenkrankheit ; Pflanzenschädling ; Temperatur ; Trockenheit ; Wachstum ; Witterung ; Düngung
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 30
    facet.materialart.
    Unknown
    Untersuchungen über die Möhrenfliege (Psila rosae F.) in Schleswig-Holstein (1950)
    In:  Nachrichtenblatt des Deutschen Pflanzenschutzdienstes, p. 171-172
    Details
    Publication Date: 1950
    Description: Bericht über die Beobachtungen zur Entwicklung und zum Auftreten der Möhrenfliege unter dem Einfluss der Witterung und der Lage KATASTER-BESCHREIBUNG: Einfluss der Witterung und der Lage auf die Befallsstärke der Fliege KATASTER-DETAIL: Delta Lichtintensität +, dann Möhrenfliegenbefall -; Delta Nied +, dann Entwicklung der Maden +; Delta Wind +, dann Befall -
    Keywords: Schleswig-Holstein ; 1948-1949 ; Insekten ; Niederschlag ; Pflanzenschädling ; Temperatur ; Trockenheit ; Wind ; Witterung ; Sonnenscheindauer ; Gemüse
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 31
    facet.materialart.
    Unknown
    Studien über die Bedeutung von Witterung und Mikroklima für den Massenwechsel der Schwarzen Bohnenlaus (Doralis fabae Scop.) (1953)
    In:  Angew. Meteorol., p. 257-275
    Details
    Publication Date: 1953
    Description: Beobachtungen zu den wichtigsten Massenwechselphasen, welche phänologisch mit Hilfe der Temperatursummenregel ausgewertet wurden sowie Beobachtungen zum Einfluss des Mikroklimas auf die Flugphase KATASTER-BESCHREIBUNG: Zusammenhang zwischen den wichtigsten Massenwechselperioden und der Temperatur, angegeben mit der mittleren Temperatursumme ab dem Eintritt des Vorfrühlings (Schneeglöckchenblüte); Einfluss von flugbegrenzenden Faktoren (Licht, Wind, Niederschlag) und flugbeeinflussenden Faktoren (Temperatur, Luftfeuchtigkeit) KATASTER-DETAIL: Temperatursumme = 160°C, dann Schlüpfen der ersten Fundatrixlarven; Temperatursumme = 360°C, dann Eintreten erster reifer Fundatrizen; Temperatursumme = 600°C, dann Reife der ersten fundatrigenen Fliegen und Anfang des fundatrigenen Zufluges; Temperatursumme = 1000-1050°C, dann Ende des fundatrigenen Zufluges und Anfang des virginogenen Zufluges; temperatursumme = 2280-2420°C, dann Ende des virginogenen Zufluges; Delta Lichtintensität + und Windgeschwindigkeit 〈 0,6m/s und T(Blattoberfläche ) 〉= 17°C, bzw. T (Luft) 〉= 15-16°C und Delta Nied -, dann Abflug +; Delta T +, dann Ablfug +, T 〉 20-26°C, dann Abflug -; Relf = 60%, dann optimaler Bereich für Abflug;
    Keywords: Quedlinburg, Thüringen ; 1949-1952 ; Luftfeuchte ; Klima ; Korrelationsmethode ; Niederschlag ; Pflanzenschädling ; Phänologie ; Temperatur ; Wind ; Witterung
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 32
    facet.materialart.
    Unknown
    Die Abhängigkeit der Aktivität des Kohlgallenrüsslers (Ceutorrhynchus pleurostigma March.) von klimatischen Faktoren (1953)
    In:  Nachrichtenblatt für den deutschen Pflanzenschutzdienst, p. 143-148
    Details
    Publication Date: 1953
    Description: Bericht über die Untersuchungen zur Frage der Abhängigkeit der Imagines von klimatischen Faktoren KATASTER-BESCHREIBUNG: Einfluss der Witterung (Temperatur, Wind, Sonnenscheindauer, Luftfeuchte) auf die Flugaktivität KATASTER-DETAIL: Delta T +: T= 18°C, dann Höchstwert an geschlüpften und geschlechtsreifen Käfern; T 〉 18°C oder T 〈 18°C, dann Zahl an geschlüpften und geschlechtsreifen Käfern -; Delta Sonn +, dann Flugaktivität +; T = 23°C und Relf = 70%, dann Optimum der Flugaktivität; T = 13°C, dann Flugaktivität verhindert Delta Wind +: Wind 〉 1m/s, dann Flugaktivität vermindert, Wind 〉 2m/s, dann Flugaktivität stark gehemmt
    Keywords: Sachsen-Anhalt ; 1951-1952 ; Insekten ; Luftfeuchte ; Korrelationsmethode ; Niederschlag ; Pflanzenschädling ; Temperatur ; Wind ; Witterung ; Sonnenscheindauer
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 33
    facet.materialart.
    Unknown
    Witterung, Wasserbilanz und Ertragsschwankungen von Feldkulturen (1950)
    In:  Archiv der wiss. Ges. f. Land- und Forstwirtschaft 2
    Details
    Publication Date: 1950
    Description: Untersuchungen zu Ertragsunterschieden bei Zuckerrüben, Kartoffeln und Hafer durch Errechnen der Wasserbilanz in einzelnen Monaten KATASTER-BESCHREIBUNG: Einfluss von Temperatur und Niederschlag (=der Wasserbilanz) auf den Ertrag von Zuckerrübe, Hafer und Kartoffel KATASTER-DETAIL: Wasserbilanz (März bis April) ausgeglichen oder leicht positiv, dann Erträge +; Wasserbilanz (Mai bis Juni) stark negativ über mindestens 25 Tage, dann Erträge +; Wasserbilanz (Juli bis September) ausgeglichen, dann Erträge +; Delta T (Frühjahr) +, dann Erträge +; Delta T +, dann Erträge (Zuckerrübe) +; Delta T (außer Juli; bes. Juni) -, dann Erträge (Hafer)+
    Keywords: Niedersachsen, Grossraum Hannover - Göttingen ; 1932-40, 1947-49 ; Kartoffeln ; Ertrag ; Hafer ; Landwirtschaft ; Niederschlag ; Temperatur ; Trockenheit ; Verdunstung ; Wassermangel
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 34
    facet.materialart.
    Unknown
    Über Beziehungen zwischen Witterungsverlauf und Ertragsleistung bei landwirtschaftlichen Kulturpflanzen im Land Brandenburg, 2. Beitrag: Sommer- und Wintergetreide (1950)
    In:  Zeitschrift für Acker- und Pflanzenbau 92:100-124.
    Details
    Publication Date: 1950
    Description: Einteilung der Witterung in Pentaden, Berechnung einer Wetterwertzahl und Bezug zum Ernteertrag KATASTER-BESCHREIBUNG: Einfluss der Witterung (Niederschlag, Temperatur) auf den Ertrag verschiedener Getreidearten (Sommerweizen, Sommergerste, Sommerroggen, Hafer, Winterweizen, Wintergerste, Winterroggen) KATASTER-DETAIL: Delta Tmit (Pentade) 〉 5°C, dann Beginn Vegetationsperiode; Delta Nied (Winter) -, dann Ertrag (Sommergetreidearten) +; Delta Nied (März) -, dann Erträge (Sommerweizen, Sommergerste) +; Delta Nied (Winter) +, dann Erträge (Wintergetreidearten) -; Delta Nied (Winter) -, dann Erträge (Winterweizen, Wintergerste) -; t (T 〉 5°C) + (früher), dann Erträge (Winterweizen, Wintergerste) +; Detaillierte Informationen zu den einzelnen Getreidearten: siehe Artikel
    Keywords: Brandenburg ; 1938-39, 1943 ; Ertrag ; Getreide ; Landwirtschaft ; Niederschlag ; Temperatur ; Weizen ; Wind ; Witterung ; Hackfrüchte
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 35
    facet.materialart.
    Unknown
    Eine Darstellung der ursächlichen Wechselbeziehungen zwischen Witterungsverlauf und Bodenzustand in ihren Auswirkungen auf Pflanzenwuchs und Ernte (1942)
    In:  Klima / Boden / Ernte Verlag C.V. Engelhard, Berlin. p. 7, 114-127
    Details
    Publication Date: 1942
    Description: Beziehung zwischen Witterungsablauf und Bodenzustand und deren Auswirkung auf Pflanzenwuchs und Ernte KATASTER-BESCHREIBUNG: Einfluss der Witterung auf den Ertrag von Kartoffeln KATASTER-DETAIL: Delta T (April bis Juli) -, dann Erträge (Kartoffel) +; Delta Nied (April bis Juli) -, dann Erträge (Kartoffel) -
    Keywords: Gesamtpreußen, Deutschland,Schlesien ; 1921-1932,1934 ; Zuckerrüben ; Kartoffeln ; Ertrag ; Hafer ; Landwirtschaft ; Niederschlag ; Temperatur ; Witterung ; Hackfrüchte
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 36
    facet.materialart.
    Unknown
    Die Zunahme wichtiger Getreideschädlinge als Folge der besonderen Witterungserscheinungen in den letzten Jahren (1950)
    In:  Pflanzenschutz, Jahrgang 2, Nr. 8, p. 95-97
    Details
    Publication Date: 1950
    Description: Beobachtungen zum Auftreten von Roggengallmücke, Halmfliege, Getreidehalmwespe, Hafermilbe und Zwergzikade unter bestimmten Witterungsbedingungen (warme und trockene Sommer und Herbste) KATASTER-BESCHREIBUNG: Einfluss der Witterung (Temperatur und Niederschlag) im Sommer und Herbst auf das Auftreten der Getreideschädlinge KATASTER-DETAIL: Delta T (Sommer und Herbst) + und Delta Nied (Sommer und Hebrst) -, dann Auftreten +; Trockenperioden über mindestens 2 Jahre, dann Massenauftreten
    Keywords: Bayern ; 1947-1950 ; Anbautermine ; Landwirtschaft ; Niederschlag ; Pflanzenschädling ; Roggen ; Temperatur ; Trockenheit ; Weizen ; Witterung
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    BIBLIOGRAPHY INKA BB
  • 37
    facet.materialart.
    Unknown
    The Development of a New Lateral-Control Arrangement (1941)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Development work on an arrangement using ailerons and spoilers for lateral control was carried out by the Vought-Sikorsky Aircraft Division of the United Aircraft Corporation on a small commercial airplane in flight and on an airfoil in a wind tunnel. Spoiler hinge moments were reduced by aerodynamic balance. The arrangement was then built into an experimental airplane and further improvements were adopted as the result of flight and tunnel tests. The use of ailerons for lateral control with flaps up, spoilers with flaps full down, and gradual transition as the flaps are lowered was found to provide lateral control under the flight conditions for which they were best suited. The ailerons were of short span, permitting the use of long-span flaps, and were drooped to a relatively large angle when the flaps were deflected. A high maximum lift coefficient was thus attained. With large control deflections in the intermediate flap-angle range and spoiler effectiveness near neutral improved by "ventilating" the spoiler, the lateral control was satisfactory for the experimental airplane and was a definite improvement over that of a conventional control arrangement.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 38
    facet.materialart.
    Unknown
    Antispin-Tail-Parachute Installations (1943)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: Although antispin tail parachutes have been used successfully in spin demonstrations for some time, very little published information is available concerning the size of parachute, the bridle-line length, and the type and location of pack to use for particular airplane. The present paper is an attempt to supply data relating to these factors. The paper is in two parts. The first part reviews the principles of operation of the antispin parachutes, views the principles of operation of the antispin parachutes, summarized available information on actual installations, and discusses parachute loads and pack locations. The second part of the paper reports on systematic tests in the NACA-15-foot and 20-foot free-spinning tunnels at the Langley memorial Aeronautical Laboratory to determine the minimum size and the optimum bridle-line lengths for antispin tail parachutes for current military airplanes. It is concluded that airplanes weighing between 7500 and 14,000 pounds require parachutes 8 feet in diameter and bridle-line lengths between 20 and 50 feet. A positive-ejection mechanism is desirable to throw the parachute clear of the tail and to assure rapid opening. The pack and attachment point must be so located that the equipment will not foul the tail surfaces.
    Keywords: Aircraft Stability and Control
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 39
    facet.materialart.
    Unknown
    Tests of the XP-46 Airplane in the N.A.C.A. Full-Scale Wind Tunnel (1940)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: An investigation has been conducted on a full-scale model of the proposed XP-46 airplane in the N. A. C. A. full-scale wind tunnel pursuant to the request of the Amy Air Corps, Materiel Division. The primary purpose of the investigation was to determine the optimum arrangement of the various component parts to obtain the maximum high speed and to provide adequate engine cooling. Additional tests included a determination of the stalling characteristics and the effectiveness of ailerons and elevators. The profile drag of the wing was ascertained by the momentum method; the location of the transition point on the wing and the critical compressibility velocities of the various airplane components were determined from surface pressure surveys.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 40
    facet.materialart.
    Unknown
    A Theoretical Investigation of Longitudinal Stability of Airplanes with Free Controls Including Effect of Friction in Control System (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The relation between the elevator hinge moment parameters and the control forces for changes in forward speed and in maneuvers is shown for several values of static stability and elevator mass balance. The stability of the short period oscillations is shown as a series of boundaries giving the limits of the stable regions in terms of the elevator hinge moment parameters. The effects of static stability, elevator moment of inertia, elevator mass unbalance, and airplane density are also considered. Dynamic instability is likely to occur if there is mass unbalance of the elevator control system combined with a small restoring tendency (high aerodynamic balance). This instability can be prevented by a rearrangement of the unbalancing weights which, however, involves an increase of the amount of weight necessary. It can also be prevented by the addition of viscous friction to the elevator control system provided the airplane center of gravity is not behind a certain critical position. For high values of the density parameter, which correspond to high altitudes of flight, the addition of moderate amounts of viscous friction may be destabilizing even when the airplane is statically stable. In this case, increasing the viscous friction makes the oscillation stable again. The condition in which viscous friction causes dynamic instability of a statically stable airplane is limited to a definite range of hinge moment parameters. It is shown that, when viscous friction causes increasing oscillations, solid friction will produce steady oscillations having an amplitude proportional to the amount of friction.
    Keywords: Aircraft Stability and Control
    Type: AD-A301267 , NACA-TR-791
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 41
    facet.materialart.
    Unknown
    Control-Surface Instability on High-Speed Airplanes (1942)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: Tests of several modern airplanes indicate that control surfaces with a high degree of aerodynamic balance are likely to possess characteristics which make them unsatisfactory or dangerous in high-speed flight. Dive tests made in the spring of 1940 at the NACA on a naval fighter-type airplane illustrate one form of instability that may be encountered. During a dive at an indicated airspeed of 365 miles per hour, the ailerons suddenly overbalanced. The efforts of the pilot to bring the ailerons back to neutral resulted in a violent oscillation of the control stick from side to side. Fortunately, the force required to return the ailerons to neutral was within the pilot's capabilities. A time history of the maneuver is given in figure1 and typical frames from motion pictures of the cockpit and of the wing, taken during the maneuver, are given in figure 2. In the illustrated case, the occurrence of aerodynamic overbalance was attributed to a slight bulge, approximately 1/16 inch thick, on the lower surface of the leading edges of the ailerons, caused by the installation of additional mass balance ahead of the hinge line. A drawing showing the shape of the bulge is given in figure 3. After this slight protuberance had been eliminated, dives were successfully made at higher speeds.
    Keywords: Aircraft Stability and Control
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 42
    facet.materialart.
    Unknown
    New Research on the Cowling and Cooling of Radial Engines (1943)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: An extensive series of wind-tunnel tests on a half-scale conventional, nacelle model were made by the United Aircraft Corporation to determine and correlate the effects of many variables on cooling air flow and nacelle drag. The primary investigation was concerned with the reaction of these factors to varying conditions ahead of, across, and behind the engine. In the light of this investigation, common misconceptions and factors which are frequently overlooked in the cooling and cowling of radial engines are considered in some detail. Data are presented to support certain design recommendations and conclusions which should lead toward the improvement of present engine installations. Several charts are included to facilitate the estimation of cooling drag, available cooling pressure, and cowl exit area.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 43
    facet.materialart.
    Unknown
    NACA Apparatus and Methods for Take-Off and Landing Measurements (1943)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: Experience has shown that the determination of the take-off and. landing characteristics of airplanes requires specialized, equipment of a high degree of precision and reliability and demands great care in the evaluation and interpretation of data. It is believed, therefore, that a description of the apparatus and methods that have been developed by the NACA for these measurements might be of considerable interest, particularly to flight-test groups that have had little experience with landing and. take-off measurements. The basic principles and essential details of the Committee's equipment are described, the methods of utilizing the apparatus and of reducing the data are explained, and sample test results are presented.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 44
    facet.materialart.
    Unknown
    Flight Determination of the Static Longitudinal Stability Boundaries of the Bell X-5 Research Airplane with 59 Deg Sweepback (1953)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: During the flight program on the Bell X-5 airplane with 59 deg sweepback to determine the practical Mach number and normal-force coefficient limits of this configuration, a reduction in static longitudinal stability was encountered in maneuvering flight. A determination of the boundary for reduction of longitudinal stability extending to a Mach number of 0.98 is presented in this paper. A reduction of static longitudinal stability existed for all elevator and all stabilizer-executed maneuvers. The reduction of stability existed for maneuvers executed with elevator near a normal-force coefficient of 0.6 for a Mach number range of about 0.31 to 0.76. Above a Mach number of 0.76 the normal-force coefficient for reduction of stability gradually decreased to a value of 0.2 at a Mach number of 0.98. For stabilizer-executed maneuvers the stability boundary was the same as for elevator maneuvers up to a Mach number of 0.88. Above this Mach number the reduction of stability occurred at slightly higher normal-force coefficients decreasing from about 0.51 at a Mach number of 0.92 to a value of 0.311 at a Mach number of 0.97. The airplane has been flown to a Mach number of 1.04 at a normal-force coefficient of about 0.15 without encountering any reduction of stability. The pilot did not consider the reduction of stability to be dangerous at altitudes above 30,000 feet; however, precise flight was impossible. At angles of attack above that at which the reduction of longitudinal stability occurred, directional instability and aileron control overbalance were encountered.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-L53A09b
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 45
    facet.materialart.
    Unknown
    Preliminary Results of Stability and Control Investigation of the Bell X-5 Research Airplane (1953)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: During the acceptance tests of the Bell X-5 airplane, measurements of the static stability and control characteristics and horizontal-tail loads were obtained by the NACA High-Speed Flight Research Station. The results of the stability and control measurements are presented in this paper. A change in sweep angle between 20 deg and 59 deg had a minor effect on the longitudinal trim, with a maximum change of about 2.5 deg in elevator deflection being required at a Mach number near 0.85; however, sweeping the wings produced a total stick-force change of about 40 pounds. At low Mach numbers there was a rapid increase in stability at high normal-force coefficients for both 20 0 and 1100 sweepback, whereas a condition of neutral stability existed for 58 0 sweepback at high normal-force coefficients. At Mach numbers near 0.8 there was an instability at normal-force coefficients above 0.5 for all sweep angles tested. In the low normal-force-coefficient range a high degree of stability resulted in high stick forces which limited the maximum load factors attainable in the demonstration flights to values under 5g for all sweep angles at a Mach number near 0.8 and an altitude of 12,000 feet. The aileron effectiveness at 200 sweepback was found to be low over the Mach number range tested.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-L52K18b
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 46
    facet.materialart.
    Unknown
    Flight Measurements of the Stability Characteristics of the Bell X-5 Research Airplane in Sideslips at 59 Deg Sweepback (1953)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flight measurements of the stability characteristics of the Bell X-5 research airplane at 59 deg sweepback were made in steady sideslips at Mach numbers from 0.62 to 0.97 at altitudes ranging between 35,000 and 40,000 feet. The results showed that the apparent directional stability was positive and increased at Mach numbers above 0.90. The apparent effective dihedral was positive and high, increasing at Mach numbers above 0.75. The cross-wind force coefficient per degree of sideslip was positive and increased rapidly at Mach numbers above 0.94.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-L52K13b
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 47
    facet.materialart.
    Unknown
    Study of Jet-Propulsion System Comprising Blower, Burner, and Nozzle (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A study was made of the performance of a jet-propulsion system composed of an engine-driven blower, a combustion chamber, and a discharge nozzle. A simplified analysis is made of this system for the purpose of showing in concise form the effect of the important design variables and operating conditions on jet thrust, thrust horsepower, and fuel consumption. Curves are presented that permit a rapid evaluation of the performance of this system for a range of operating conditions. The performance for an illustrative case of a power plant of the type under consideration id discussed in detail. It is shown that for a given airplane velocity the jet thrust horsepower depends mainly on the blower power and the amount of fuel burned in the jet; the higher the thrust horsepower is for a given blower power, the higher the fuel consumption per thrust horsepower. Within limits the amount of air pumped has only a secondary effect on the thrust horsepower and efficiency. A lower limit on air flow for a given fuel flow occurs where the combustion-chamber temperature becomes excessive on the basis of the strength of the structure. As the air-flow rate is increased, an upper limit is reached where, for a given blower power, fuel-flow rate, and combustion-chamber size, further increase in air flow causes a decrease in power and efficiency. This decrease in power is caused by excessive velocity through the combustion chamber, attended by an excessive pressure drop caused by momentum changes occurring during combustion.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-E-212 , NACA-ACR-E4E06
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 48
    facet.materialart.
    Unknown
    Tests of Thermal-electric De-icing Equipment for Propellers (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flights were made in natural icing conditions at the NACA Ice Research Project, Minneapolis, Minn. to test several designs of thermal-electric propeller de-icing blade shoes and a hub-generator design. It was found that a minimum average unit power of 2.5 watts per square inch of blade-shoe area would protect the propeller blades at the test conditions. The most satisfactory blade shoe of the three designs tested extended to the 20-percent-chord point and to 90 percent of the blade radius. A concentration of heat in the leading-edge region of this shoe was found to reduce the power input necessary for satisfactory de-icing. A satisfactory thermal design of blade shoe and a hub generator of sufficient capacity were developed.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-A-47 , NACA-ARR-4A20
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 49
    facet.materialart.
    Unknown
    Effect of Changes in Aileron Rigging on the Stick Forces of a High-Speed Fighter Airplane (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effects of changes in aileron rigging between 2 deg up and 2 deg down on the stick forces were determined from wind-tunnel data for a finite-span wing model. These effects were investigated for ailerons deflecting equally in both directions and linearly with stick deflection. Data were analyzed for a Frise, a sealed internally balanced, and a beveled-trailing-edge aileron. The results of the analysis showed that only ailerons having linear hinge-moment characteristics are unaffected by changes in rigging and indicated that ailerons having decidedly nonlinear hinge-moment-coefficient curves, particularly for deflections near 0 deg, are very sensitive to changes in rigging.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-289 , NACA-RB-L4E11
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 50
    facet.materialart.
    Unknown
    Wind-Tunnel Investigation of Perforated Split Flaps for Use as Dive Brakes on a Tapered NACA 23012 Airfoil (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Aerodynamic characteristics of a tapered NACA 23012 airfoil with single and double perforated split flaps have been determined in the NACA 7- by 10-foot wind tunnel. Dynamic pressure surveys were made behind the airfoil at the approximate location of the tail in order to determine the extent and location of the wake for several of the flap arrangements. In addition, computations have been made of an application of perforated double split flaps for use as fighter brakes. The results indicated that single or double perforated split flaps may be used to obtain satisfactory dive control without undue buffeting effects and that single or double perforated split flaps may also be used as fighter brakes. The perforated split flaps had approximately the same effects on the aerodynamic and wake characteristics of the tapered airfoil as on a comparable rectangular airfoil.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-373
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 51
    facet.materialart.
    Unknown
    Wind Tunnel Investigation of the Effect of Jet-Motor Operation Stability (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effects of jet-motor operation on the stability and control characteristics of two fighter-type airplanes as determined by wind-tunnel tests of 1/5-scale models are presented. It is shown that the action of the jets is to cause a small loss in stick-fixed stability which is predictable from known theories.
    Keywords: Aircraft Stability and Control
    Type: NACA-WR-A-31
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 52
    facet.materialart.
    Unknown
    Fuselage Pressures Measured on the Bell X-1 Research Airplane in Transonic Flight (1953)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Pressure-distribution measurements have been made on the fus elage of the Bell X- 1 research airplane. Data are presented for angles of attack from 2 deg. to 8 deg. during pull-ups at Mach numbers of about 0.78, 0.85, 0.88, and 1.02. The results of the investigation indicated that a large portion of the load carried by the fuselage was in the vicinity of the wing and may be attributed to wing-to-fuselage carryover. The presence of the wing from the 41 to 60 percent fuselage stations influenced the fuselage pressures from about 30 to 65 percent fuselage length at Mach numbers of approximat ely 0.78, 0.85, and 0.88, and from about 35 to 80 percent fuselage length at a Mach number of approximately 1.02. The fuselage contributed about 20 percent of the total airplane normal-force coefficient. The center of pressure of the fuselage load throughout the tests was located from 41 to 51 percent fuselage length, which corresponds to the forward half of the wing root-chord location.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L53I15
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 53
    facet.materialart.
    Unknown
    Cooling Tests of an Airplane Equipped with an NACA Cowling and a Wing-duct Cooling System (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Cooling tests were made of a Northrop A-17A attack airplane successively equipped with a conventional.NACA cowling and with a wing-duct cooling system. The method of cooling the engine by admitting air from the propeller slipstream into wing ducts, passing it first through the accessory compartment and then over the engine from rear to front, appeared to offer possibilities for improved engine cooling, increased cooling of the accessories, and better fairing of the power-plant installation. The results showed that ground cooling for the wing duct system without cowl flap was better than for the NACA cowling with flap; ground cooling was appreciably improved by installing a cowl flap. Satisfactory temperatures were maintained in both climb and high-speed flight, but, with the use of conventional baffles, a greater quantity of cooling air appeared to be required for the wing duct system.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-813
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 54
    facet.materialart.
    Unknown
    Effect of a Rapid Blade-Pitch Increase on the Thrust and Induced-Velocity Response of a Full-Scale Helicopter Rotor (1953)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A method has been proposed for predicting the effect of a rapid blade-pitch increase on the thrust and induced-velocity response of a helicopter rotor. General equations have been derived for the ensuing motion of the helicopter. These equations yield time histories of thrust, induced velocity, and helicopter vertical velocity for given rates of blade-pitch-angle changes and given rotor-angular-velocity time histories. The results of the method have been compared with experimental results obtained with a rotor mounted on the Langley helicopter test tower. The calculated and experimental results are in good agreement, although, in general, the calculated thrust-coefficient overshoots are about 10 percent greater than those obtained experimentally.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-3044
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 55
    facet.materialart.
    Unknown
    Effect of Mach Number on the Flow and Application of Compressibility Corrections in a Two-Dimensional Subsonic-Transonic Compressor Cascade Having Varied Porous-Wall Suction at the Blade Tips (1952)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A cascade of 65-(12)10 compressor blades was tested at one geometric setting over a range of inlet Mach number from 0.12 to 0.89. Two groups of data are presented and compared: the first from the cascade operating conventionally with no boundary-layer control, and the second with the boundary layer controlled by a combination of upstream slot suction and porous-wall suction at the blade tips. A criterion for two-dimensionality was used to specify the degree of boundary-layer control by suction to be applied. The data are presented and an analysis is made to show the effect of Mach number on turning angle, blade wake, pressure distribution about the blade profile and static-pressure rise. The influence of boundary-layer control on these parameters as well as on the secondary losses is illustrated. A system of correlating the measured static-pressure rise through the cascade with the theoretical isentropic values is presented which gives good agreement with the data. The pressure distribution about the blade profile for an inlet Mach number of 0.21 is corrected with the Prandtl-Glauert, Karman-Tsien, and vector-mean velocity - contraction coefficient compressibility correction factors to inlet Mach numbers of 0.6 and 0.7. The resulting curves are compared with the experimental pressure distributions for inlet Mach numbers of 0.6 and 0.7 so that the validity of applying the three corrections can be evaluated.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-2649
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 56
    facet.materialart.
    Unknown
    Empirical Relation Between Induced Velocity, Thrust, and Rate of Descent of a Helicopter Rotor as Determined by Wind-tunnel Tests on Four Model Rotors (1951)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The empirical relation between the induced velocity, thrust, and rate of vertical descent of a helicopter rotor was calculated from wind tunnel force tests on four model rotors by the application of blade-element theory to the measured values of the thrust, torque, blade angle, and equivalent free-stream rate of descent. The model tests covered the useful range of C(sub t)/sigma(sub e) (where C(sub t) is the thrust coefficient and sigma(sub e) is the effective solidity) and the range of vertical descent from hovering to descent velocities slightly greater than those for autorotation. The three bladed models, each of which had an effective solidity of 0.05 and NACA 0015 blade airfoil sections, were as follows: (1) constant-chord, untwisted blades of 3-ft radius; (2) untwisted blades of 3-ft radius having a 3/1 taper; (3) constant-chord blades of 3-ft radius having a linear twist of 12 degrees (washout) from axis of rotation to tip; and (4) constant-chord, untwisted blades of 2-ft radius. Because of the incorporation of a correction for blade dynamic twist and the use of a method of measuring the approximate equivalent free-stream velocity, it is believed that the data obtained from this program are more applicable to free-flight calculations than the data from previous model tests.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-2474
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 57
    facet.materialart.
    Unknown
    An Analysis of the Autorotative Performance of a Helicopter Powered by Rotor-Tip Jet Units (1950)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The autorotative performance of an assumed helicopter was studied to determine the effect of inoperative jet units located at the rotor-blade tip on the helicopter rate of descent. For a representative ramjet design, the effect of the jet drag is to increase the minimum rate of descent of the helicopter from about 1,OO feet per minute to 3,700 feet per minute when the rotor is operating at a tip speed of approximately 600 feet per second. The effect is less if the rotor operates at lower tip speeds, but the rotor kinetic energy and the stall margin available for the landing maneuver are then reduced. Power-off rates of descent of pulse-jet helicopters would be expected to be less than those of ramjet. helicopters because pulse jets of current design appear to have greater ratios of net power-on thrust to power-off, drag than currently designed rain jets. Iii order to obtain greater accuracy in studies of autorotative performance, calculations in'volving high power-off rates of descent should include the weight-supporting effect of the fuselage parasite-drag force and the fact that the rotor thrust does not equal the weight of the helicopter.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-2154
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 58
    facet.materialart.
    Unknown
    Effects of Propeller Operation and Angle of Yaw on the Distribution of the Load on the Horizontal Tail Surface of a Typical Pursuit Airplane (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aircraft Stability and Control
    Type: NACA-WR-L-227 , NACA-ARR-4B10
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 59
    facet.materialart.
    Unknown
    Wind-Tunnel Tests of the 1/9-Scale Model of the Curtiss XP-62 Airplane with Various Vertical Tail Arrangements (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effect of various vertical tail arrangements upon the stability and control characteristics of an XP-62 fighter model was investigated. Rudder-free yaw characteristics with take-off power and flaps deflected were satisfactory after dorsal fin modifications. Directional stability was obtained with all modified vertical tails. Satisfactory rudder effectiveness resulted partly because the dual-rotation propellers produced no asymmetric yawing moments. Pedal forces in sideslips were undesirably large but may be easily reduced.
    Keywords: Aircraft Stability and Control
    Type: NACA-WR-L-779
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 60
    facet.materialart.
    Unknown
    Secondary Stresses in Open Box Beams Subjected to Torsion (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In open box beams subjected to torsion, secondary stresses arise owing to lateral bending of the spar caps. The present paper outlines a simple method for estimating the magnitude of these stresses and gives the results of tests of an open box beam in the neighborhood of a discontinuity where the cover changed from the top to the bottom of the box.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-14 , NACA-ARR-L4I23
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 61
    facet.materialart.
    Unknown
    Preliminary Investigation in the NACA Low-Turbulence Tunnel of Low-drag Airfoil Sections Suitable for Admitting Air at the Leading Edge (1942)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was carried out in the NACA low-turbulence tunnel to develop low-drag airfoil sections suitable for admitting air at the leading edge. A thickness distribution having the desired type of pressure distribution was found from tests of a flexible model. Other airfoil shapes were derived from this original shape by varying the thickness, the camper, the leading-edge radius, and the size of the leading-edge opening. Data are presented giving the characteristics of the airfoil shapes in the range of lift coefficients for high-speed and cruising flight. Shapes have been developed which show no substantial increases in drag over that of the same position along the chord. Many of these shapes appear to have higher critical compressibility speeds than plain airfoils of the same thickness. Low-drag airfoil sections have been developed with openings in the leading edge as large as 41.5 percent of the maximum thickness. The range of lift coefficients for low drag in several cases is nearly as large as that of the corresponding plain airfoil sections. Preliminary measurements of maximum lift characteristics indicate that nose-opening sections of the type herein considered may not produce any marked effects on the maximum lift coefficient.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-694
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 62
    facet.materialart.
    Unknown
    Investigation of Diving Moments of a Pursuit Airplane in the Ames 16-Foot High Speed Wind Tunnel (1942)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A pursuit type airplane encountered severe diving moments in high-speed dives which make recovery difficult. For the purpose of investigating these diving moments and finding means for their reduction, a 1/6-scale model of the airplane was tested in the 16-foot high-speed wind tunnel at Ames Aeronautical Laboratory. The test results indicate that up to a Mach number of at least 0.75, the limit of the tests, the dive-recovery difficulties can be alleviated and the longitudinal maneuverability improved by the substitution of a long symmetrical fuselage for the standard fuselage.
    Keywords: Aircraft Stability and Control
    Type: NACA-WR-A-65
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 63
    facet.materialart.
    Unknown
    Control-Motion Studies of the PBM-3 Flying Boat in Abrupt Pull-Ups (1942)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-577 , AD-A801579
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 64
    facet.materialart.
    Unknown
    Design of power-plant installations pressure-loss characteristics of duct components (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A correlation of what are believed to be the most reliable data available on duct components of aircraft power-plant installations is presented. The information is given in a convenient form and is offered as an aid in designing duct systems and, subject to certain qualifications, as a guide in estimating their performance. The design and performance data include those for straight ducts; simple bends of square, circular, and elliptical cross sections; compound bends; diverging and converging bends; vaned bends; diffusers; branch ducts; internal inlets; and an angular placement of heat exchangers. Examples are included to illustrate methods of applying these data in analyzing duct systems. (author)
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-208 , NACA-ARR-L4F26
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 65
    facet.materialart.
    Unknown
    Resume of Data for Internally Balanced Ailerons (1943)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: The available test results of internally balanced ailerons have been correlated and summarized herein. Although several variables have yet to-be-investigated, the results presented will be useful in the preliminary design of internally balanced ailerons and in the determination of the most promising modifications to unsatisfactory ailerons.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 66
    facet.materialart.
    Unknown
    Flight Tests of the Wilford XOZ-1 Sea Gyroplane (1941)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: During August 1939 a series of flight tests was made at Langley Field on the Wilford sea gyroplane, designated by the Navy as the XOZ-1. These tests were intended to permit rough evaluation of the stability and control characteristics of the machine, with particular reference to possible improvements in rigging which might be made in future machines with fixed wing and nonarticulated feathering control rotor, and to provide data on the bending and feathering motions of the rotor blades. The tests made in 1939 proved inadequate, chiefly because the machine as flown did not have sufficient propeller thrust to give it an appreciable speed range in steady flight. Further tests were therefore made in August 1940 after overhauling the engine and substituting a metal propeller for the wooded one first used. The range of speeds covered in steady flight was markedly extended. Steady-flight runs only were made in this series, since it was felt that takeoffs and landings had been covered sufficiently in the previous tests.
    Keywords: Aircraft Stability and Control
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 67
    facet.materialart.
    Unknown
    Comparison of Aileron Control Characteristics as Determined in Flight Tests of P-36, P-40, Spitfire, and Hurricane Pursuit Airplanes (1942)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: The Army Air Force has made available several pursuit-type airplanes for quantitative investigation of their flying and handling qualities. One Item of special interest obtained from the results of the investigation is a comparison of the aileron control characteristics of the P-36, P-40, Hawker Hurricane, and Supermarine Spitfire airplanes. Figure 1 shows the design characteristics of the ailerons and the control sticks of the four airplanes. Aileron effectiveness may be expressed in terms of the helix angle generated by the wing tip in a steady roll. This angle is given by the expression pb/2V, where p is the rolling velocity, b the wing span, and V the true airspeed, expressed in consistent units. This quantity is convenient to use because, although it does not rep resent directly the rolling velocity of airplanes of different spans or airplanes operating at different speeds, it provides a satisfactory basis for computing the rate of roll and the time required to bank a given amount under any given set of conditions. The ratio of pb/2V obtained in any roll to the maximum value reached with full aileron deflection indicates the fraction of the maximum aileron travel that was reached. A complete discussion of this criterion for aileron effectiveness is given in reference 1. The aileron effectiveness of the various airplanes is compared in the following table on the basis of the response obtained with stick forces of 30 and 5 pounds. A force of 30 pounds is somewhat less than the greatest stick force exerted by the pilot. Repeated flight measurements have shown, however, that this force is a reasonable upper limit for maneuvering at high speeds.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 68
    facet.materialart.
    Unknown
    The Effect of Blunt-Trailing-Edge Modifications on the High-Speed Stability and Control Characteristics of a Swept-Wing Fighter Airplane (1954)
    In:  CASI
    Details
    Publication Date: 2019-05-25
    Description: An investigation was conducted on a 35 deg swept-wing fighter airplane to determine the effects of several blunt-trailing-edge modifications to the wing and tail on the high-speed stability and control characteristics and tracking performance. The results indicated significant improvement in the pitch-up characteristics for the blunt-aileron configuration at Mach numbers around 0.90. As a result of increased effectiveness of the blunt-trailing-edge aileron, the roll-off, customarily experienced with the unmodified airplane in wings-level flight between Mach numbers of about 0.9 and 1.0 was eliminated, The results also indicated that the increased effectiveness of the blunt aileron more than offset the large associated aileron hinge moment, resulting in significant improvement in the rolling performance at Mach numbers between 0.85 and 1.0. It appeared from these results that the tracking performance with the blunt-aileron configuration in the pitch-up and buffeting flight region at high Mach numbers was considerably improved over that of the unmodified airplane; however, the tracking errors of 8 to 15 mils were definitely unsatisfactory. A drag increment of about O.OOl5 due to the blunt ailerons was noted at Mach numbers to about 0.85. The drag increment was 0 at Mach numbers above 0.90.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-A54C31
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 69
    facet.materialart.
    Unknown
    A Study of the Effect of Increased Size and Speed of Pursuit Airplanes on the Aileron Balancing Problem (1942)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: The present trend is toward faster and larger pursuit airplanes. Because both speed and size increase the aileron control forces, the design of ailerons for manual operation is becoming increasingly difficult. In order to obtain a clearer picture of the future problem of balancing ailerons, and inspection has been made of the effects of airplane size and speed on the control forces. Computations were made of the aileron control forces required to meet specified rolling conditions for plain ailerons on wings with spans from 40 to 80 feet and for speeds up to 500 miles per hour. The rolling conditions were specified by two alternative criterions. One was the rolling criterion pb/2V of reference 1. For reasons, which will be discussed later, a value of 0.09 rather than the recommended value of 0.07 was assigned to this criterion. For the criterion pb/2V, the required value of the rolling velocity p varies inversely with the airplane span b. There is some question as to whether the rolling velocity of a pursuit airplane can be permitted to decrease simply because its size is increased. For the second criterion, therefore, the rolling velocity is independent of span (p/V is a constant). The value assigned to this criterion was so chosen that for a wing of 40-foot span the value of pb/2V would be 0.09. The computations neglected compressibility effects. Available experimental data and the results of tests given in reference 2 indicate that the effect of compressibility is to increase the control force. Recent flight tests have indicated that, with certain types of aileron, serious compressibility effects may cause discontinuity at speeds of approximately 400 miles per hour in the aileron control force curves.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 70
    facet.materialart.
    Unknown
    Experimental Verification of the Rudder-Free Stability Theory for an Airplane Model Equipped with Rudders Having Negative Floating Tendency and Negligible Friction (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation has been made in the Langley free-flight tunnel to obtain an experimental verification of the theoretical rudder-free stability characteristics of an airplane model equipped with conventional rudders having negative floating tendencies and negligible friction. The model used in the tests was equipped with a conventional single vertical tail having rudder area 40 percent of the vertical tail area. The model was tested both in free flight and mounted on a strut that allowed freedom only in yaw. Tests were made with three different amounts of rudder aerodynamic balance and with various values of mass, moment of inertia, and center-of-gravity location of the rudder. Most of the stability derivatives required for the theoretical calculations were determined from forced and free-oscillation tests of the particular model tested. The theoretical analysis showed that the rudder-free motions of an airplane consist largely of two oscillatory modes - a long-period oscillation somewhat similar to the normal rudder-fixed oscillation and a short-period oscillation introduced only when the rudder is set free. It was found possible in the tests to create lateral instability of the rudder-free short-period mode by large values of rudder mass parameters even though the rudder-fixed condition was highly stable. The results of the tests and calculation indicated that for most present-day airplanes having rudders of negative floating tendency, the rudder-free stability characteristics may be examined by simply considering the dynamic lateral stability using the value of the directional-stability parameter Cn(sub p) for the rudder-free condition in the conventional controls-fixed lateral-stability equations. For very large airplanes having relatively high values of the rudder mass parameters with respect to the rudder aerodynamic parameters, however, analysis of the rudder-free stability should be made with the complete equations of motion. Good agreement between calculated and measured rudder-free stability characteristics was obtained by use of the general rudder-free stability theory, in which four degrees of lateral freedom are considered. When this assumption is made that the rolling motions alone or the lateral and rolling motions may be neglected in the calculations of rudder-free stability, it is possible to predict satisfactorily the characteristics of the long-period (Dutch roll type) rudder-free oscillation for airplanes only when the effective-dihedral angle is small. With these simplifying assumptions, however, satisfactory prediction of the short-period oscillation may be obtained for any dihedral. Further simplification of the theory based on the assumption that the rudder moment of inertia might be disregarded was found to be invalid because this assumption made it impossible to calculate the characteristics of the short-period oscillations.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-184 , NACA-ARR-L4J05A
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 71
    facet.materialart.
    Unknown
    Some Notes on the Determination of the Stick-Free Neutral Point from Wind-Tunnel Data (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Two graphical methods are presented for determining the stick-free neutral point, and they are extensions of the methods commonly used to determine the stick-free neutral point. A mathematical formula for computing the stick-free neutral point is also given. These methods may be applied to determine approximately the increase in tail size necessary to shift the neutral point (stick fixed or free) to any desired location on an airplane having inadequate longitudinal stability.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-251 , NACA-RB-4B21
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 72
    facet.materialart.
    Unknown
    Stall Characteristics Obtained from Flight 10 of Northrop X-4 No. 2 Airplane (USAF No. 46-677) (1950)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: NACA instrumentation has been installed ii the X-J4 airplanes to obtain stability and control data during the acceptance tests conducted by the Northrop Aircraft Corporation. This report presents data obtained on the stalling characteristics of the airplane in the clean and gear- down configurations. The center of gravity was located at approximately 18 percent of the mean aerodynamic chord during the tests. The results indicated that the airplane was not completely stalled when stall was gradually approached during nominally U accelerated flight but that it was completely stalled during a more abruptly approached stall in accelerated flight. The stall in accelerated flight was relatively mild, and this was attributed to the nature of the variation of lift with angle of attack for the 001-614 airfoil section, the plan form of the wing, and to the fact that the initial sideslip at the stall produced (as shown by wind-tunnel tests of a model of the airplane) a more symmetrical stall pattern.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-A50A04
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 73
    facet.materialart.
    Unknown
    Power-Off Tests of the Northrop N9M-2 Tailless Airplane in the 40- by 80-foot Wind Tunnel (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-MR-A4L14
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 74
    facet.materialart.
    Unknown
    Experimental Investigation of Impact in Landing on Water (1943)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The extent of agreement of the theoretical impact computations with the actual phenomenon has not as yet been fully clarified. There is on the one hand a certain imperfection in the theory (simplifying assumptions made) and on the other an insufficiency in the experimental data available. The object of our present paper is to show how far test results agree with the available approximate computation methods, to investigate in greater detail the physical nature of impact on water, and to perfect the experimental method of studying the phenomenon.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1046 , ; 438
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 75
    facet.materialart.
    Unknown
    The Effect of Several Armament Installations on the Drag of 1/8-Scale Model of the B-32 Airplane (1944)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The effect of several armament installations on the drag of a 1/8 scale model of the B-32 airplane was determined. Turrets in the following positions were tested: nose, tail, upper forward, upper aft, and lower. The nose and tail turrets were each equipped with two.50-caliber guns. Upper turrets were of three types: two.50-caliber guns, four.50-caliber guns, and 20-millimeter cannon. Lower turrets were of two types: two.50-caliber guns and four.50-caliber guns. The effect of streamlining the upper two- and four-gun turrets and of extending the lower two-gun turret was determined. The tests were conducted in the Langley 19-foot. pressure tunnel at a Reynolds number of approximately 2,960,000 and a Mach number of 0.13. Large increases in drag coefficient were caused by the complete armament installations. At a lift coefficient of 0. 4 the installations with nonstreamlined upper turrets and the lower turret retracted increased the drag coefficient by 0.0022 and 0.0027 for the two-gun and four-gun turret installations, respectively. Streamlining the upper turrets reduced the drag of these installations by approximately 40 percent with the upper turrets streamlined, the drag increase was about the same for either the two- or four-gun turret installation. The streamlined two-cannon upper turrets increased the drag about the same amount as the two-gun upper turrets that were not streamlined. Extension of the lower turret. increased the drag slightly more than the whole streamlined gun-turret installation.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-MR-L4L30a
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 76
    facet.materialart.
    Unknown
    A Flight Investigation of the Damping in Roll and Rolling Effectiveness Including Aeroelastic Effects of Rocket Propelled Missile Models Having Cruciform, Triangular, Interdigitated Wings and Tails (1951)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The damping in roll and rolling effectiveness of two models of a missile having cruciform, triangular, interdigitated wings and tails have been determined through a Mach number range of 0.8 to 1.8 by utilizing rocket-propelled test vehicles. Results indicate that the damping in roll was relatively constant over the Mach umber range investigated. The rolling effectiveness was essentially constant at low supersonic speeds and increased with increasing mach numbers in excess of 1.4 over the Mach number range investigated. Aeroelastic effects increase the rolling-effectiveness parameters pb/2V divided by delta and decrease both the rolling-moment coefficient due to wing deflection and the damping-in-roll coefficient.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L51D16
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 77
    facet.materialart.
    Unknown
    Flight Measurements of Average Skin-Friction Coefficients on a Parabolic Body of Revolution (NACA RM-10) at Mach Numbers from 1.0 to 3.7 (1954)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Measurement of average skin-friction coefficients have been made on six rocket-powered free-flight models by using the boundary-layer rake technique. The model configuration was the NACA RM-10, a 12.2-fineness-ratio parabolic body of revolution with a flat base. Measurements were made over a Mach number range from 1 to 3.7, a Reynolds number range 40 x 10(exp 6) to 170 x 10(exp 6) based on length to the measurement station, and with aerodynamic heating conditions varying from strong skin heating to strong skin cooling. The measurements show the same trends over the test ranges as Van Driest's theory for turbulent boundary layer on a flat plate. The measured values are approximately 7 percent higher than the values of the flat-plate theory. A comparison which takes into account the differences in Reynolds number is made between the present results and skin-friction measurements obtained on NACA RM-10 scale models in the Langley 4- by 4-foot supersonic pressure tunnel, the Lewis 8- by 6-foot supersonic tunnel, and the Langley 9-inch supersonic tunnel. Good agreement is shown at all but the lowest tunnel Reynolds number conditions. A simple empirical equation is developed which represents the measurements over the range of the tests.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L54G14
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 78
    facet.materialart.
    Unknown
    Strain-Gage Measurements of Buffeting Loads on a Jet-Powered Bomber Airplane (1951)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Buffet boundaries, buffeting-load increments for the stabilizers and elevators, and buffeting bending-moment increments for the stabilizers and wings as measured in gradual maneuvers for a jet-powered bomber airplane are presented. The buffeting-load increments were determined from strain-gage measurements at the roots or hinge supports of the various surfaces considered. The Mach numbers of the tests ranged from 0.19 to 0.78 at altitudes close to 30,000 feet. The predominant buffet frequencies were close to the natural frequencies of the structural components. The buffeting-load data, when extrapolated to low-altitude conditions, indicated loads on the elevators and stabilizers near the design limit loads. When the airplane was held in buffeting, the load increments were larger than when recovery was made immediately.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-L50I06
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 79
    facet.materialart.
    Unknown
    Effects of Wing Leading-Edge Camber and Tip Modifications on the Aerodynamic Characteristics of a 1/20-Scale Model of the Convair F-102 Airplane at Transonic Speeds (1954)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The effects of several wing leading-edge camber and deflected-tip modifications on the force and moment characteristics of a 1/20-scale model of the Convair F-102 airplane have been determined at Mach numbers from 0.60 t o 1.14 for angles of attack up to 14 deg. in the Langley 8-foot transonic tunnel. The effects of elevator deflections from 0 deg. to -10 deg. were also obtained for a configuration incorporating favorable leading- edge and tip modifications. Leading-edge modifications which had a small amount of constant-chord camber obtained by vertically adjusting the thickness distribution over the forward (3.9 percent of the mean aerodynamic chord) portion of the wing were ineffective in reducing the drag at lifting conditions at transonic speeds. Leading edges with relatively large cambers designed to support nearly elliptical span load distributions at lift coefficients of 0.15 and 0.22 near a Mach number of 1.0 produced substantial reductions in drag at most lift coefficients.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL54K29
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 80
    facet.materialart.
    Unknown
    Wind-Tunnel Investigation of the Static Longitudinal Stability Characteristics of a 0.15-Scale Model of the Hermes A-1E2 Missile at High Subsonic Mach Numbers (1952)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The static longitudinal stability characteristics of a 0.15-scale model of the Hermes A-lE2 missile have been determined in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.50 to 0.98, corresponding to Reynolds numbers, based on body length, of 12.3 x 10(exp 6) to 17.1 x 10(exp 6). This paper presents results obtained with body alone and body-fins combinations at 0 degrees (one set of fins vertical and the other set horizontal) and 45 degree angle of roll. The results indicate that the addition of the fins to the body insures static longitudinal stability and provides essentially linear variations of the lift and pitching moment at small angles of attack throughout the Mach number range. The slopes of the lift and pitching-moment curves vary slightly with Mach number and show only small effects due to the angle of roll.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL52I10
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 81
    facet.materialart.
    Unknown
    Tank Investigation of the Grumman JRF-5 Airplane Equipped with Twin Hydro-Skis TED No. NACA DE 357 (1951)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A tank investigation has been conducted on a 1/8-size powered dynamic model of the Grumman JRF-5 airplane equipped with twin hydro-skis. The results of tests using two types of skis are presented: one had vertical sides joining the top surface to the chine; the other had the top surface faired to the chine to eliminate the vertical sides. Both configurations had satisfactory longitudinal stability although the model had a slightly greater stable elevator range available when the skis without the vertical sides were attached. Free model tests indicated no instability present when one ski emerged before the other. Considerable excess thrust was available at all speeds with either type of skis. A hump gross load-resistance ratio of 3.37 was obtained with the skis with the vertical sides and 3.53 with the other skis. Landing behavior in smooth water with yaw up to 15deg and roll up to 15deg in opposite directions was satisfactory with either type of skis.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA RM-SL52D17
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 82
    facet.materialart.
    Unknown
    Summary of Low-Lift Drag and Directional Stability Data from Rocket Models of the Douglas XF4D-1 Airplane with and without External Stores and Rocket Packets at Mach Numbers from 0.8 to 1.38 TED No. NACA DE-349 (1952)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: At the request of the Bureau of Aeronautics, Department of the Navy, an investigation at transonic and low supersonic speeds of the drag and longitudinal trim characteristics of the Douglas XF4D-1 airplane is being conducted by the Langley Pilotless Aircraft Research Division. The Douglas XF4D-1 is a jet-propelled, low-aspect-ratio, swept-wing, tailless, interceptor-type airplane designed to fly at low supersonic speeds. As a part of this investigation, flight tests were made using rocket- propelled 1/10- scale models to determine the effect of the addition of 10 external stores and rocket packets on the drag at low lift coefficients. In addition to these data, some qualitative values of the directional stability parameter C(sub n beta) and duct total-pressure recovery are also presented.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL52G11
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 83
    facet.materialart.
    Unknown
    Low-Speed Investigation of the Static Lateral Stability and Control Characteristics of a 1/6-Scale Model of the Republic XF-84H Airplane with the Propeller Operating (1953)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation was made to determine the static lateral stability and control characteristics of a l/6-scale model of the Republic XF-84H airplane with the propeller operating. The model had a 40deg swept wing of aspect ratio 3.45 and had a thin 3-blade supersonic-type propeller. Many modifications to the basic configuration were investigated in attempts to alleviate lateral and directional trim problems which appeared to be associated with propeller slipstream rotation. Although significant benefits were realized with several modifications, none of those tested would be expected to afford satisfactory behavior for all normal flight conditions. A marked left-wing roll-off tendency was indicated at high angles of attack for the basic model configuration. Projection of only the left slat was the most effective remedy found for this problem with the propeller operating. The use of differential wing-flap deflection also appeared to offer a promising means for reducing the roll-off tendency with power on. The large sidewash over the vertical tail, associated with slip- stream rotation, severely restricted the conditions for which directional , trim could be maintained. A small triangular dorsal fin, oriented opposite to the slipstream rotation, was found very effective in reducing the adverse sidewash flow at the tail.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL53G10
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 84
    facet.materialart.
    Unknown
    Investigation of the Low-Speed Stability and Control Characteristics of a 1/10-Scale Model of the Convair YF-102 Airplane in the Langley Free-Flight Tunnel (1953)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation of the low-speed, power-off stability and control characteristics of a 1/10-scale model of the Convair YF-102 airplane has been made in the Langley free-flight tunnel. The model was flown over a lift-coefficient range from 0.5 to the stall in its basic configuration and with several modifications involving leading-edge slats and increases in vertical-tail size. Only relatively low-altitude conditions were simulated and no attempt was made to determine the effect of freeing the controls. The longitudinal stability characteristics of the model were considered satisfactory for all conditions investigated. The lateral stability characteristics were considered satisfactory for the basic configuration over the speed range investigated except near the stall, where large values of static directional instability caused the model to be directionally divergent. The addition of leading-edge slats or an 8-percent increase in vertical-tail area increased the angle of attack at which the model became directionally divergent. The use of leading-edge slats in combination with a 40-percent increase in vertical-tail size eliminated the directional divergence and produced satisfactory stability characteristics through the stall. The longitudinal and lateral control characteristics were generally satisfactory. Although the adverse sideslip characteristics for the model were considered satisfactory over the angle-of-attack range, analysis indicates that the adverse sideslip characteristics of the airplane may be objectionable at high angles of attack.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL53L04
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 85
    facet.materialart.
    Unknown
    Wind-Tunnel Investigation at Low Speed of the Pitching Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373 (1953)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An experimental investigation has been conducted in the Langley stability tunnel at low speed to determine the pitching stability derivatives of a 1/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient, control deflections, and propeller blade angle were investigated. The tests were made through an angle-of-attack range from about -4deg to 29deg, and the thrust coefficient range was from 0 to 0.7. In order to expedite distribution of these data, no analysis of the data has been prepared for this paper.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL53G27
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 86
    facet.materialart.
    Unknown
    Investigation of the Effects of Propeller Operation on the Low-Speed Stability and Control Characteristics of a 1/6-Scale Model of a Revised Configuration of the Republic XF-84H Airplane (1953)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation was made to determine the static longitudinal and lateral stability and control characteristics of a l/6-scale model of the revised Republic XF-84H airplane with and without the propeller operating. The model had a 40deg swept wing of aspect ratio 3.45 and was equipped with a thin, three-blade supersonic-type propeller. Modifications incorporated in the revised model included a raised horizontal tail, increased rudder size, wing fences at 65 percent semispan, and a modified wing leading edge outboard of the fences. The test results for flap-retracted and flap-deflected conditions indicated that the revised configuration should be satisfactory for most normal flight conditions provided the angle of attack does not exceed the angle for pitch-up. An abrupt pitch-up tendency of the model was evident for the zero thrust condition above approximately 15' angle of attack. Although the effects of power were destabilizing, power-on longitudinal stability was satisfactory through the angle-of-attack range for which the model was stable with zero thrust. Above the angle of attack for pitch-up, an uncontrollable left roll-off tendency would be expected with power on and slats retracted. Projection of wing slats or use of leading-edge chord-extensions with only the left extension drooped were found beneficial in controlling the roll-off tendency with power on; however the most effective means found was projection of only the left slat.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL53I24
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 87
    facet.materialart.
    Unknown
    Determination of the Mass Moments and Radii of Inertia of the Sections of a Tapered Wing and the Center-of-Gravity Line along the Wing Span (1943)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: For computing the critical flutter velocity of a wing among the data required are the position of the line of centers of gravity of the wing sections along the span and the mass moments and radii of inertia of any section of the wing about the axis passing through the center of gravity of the section. A sufficiently detailed computation of these magnitudes even if the weights of all the wing elements are known, requires a great deal of time expenditure. Thus a rapid competent worker would require from 70 to 100 hours for the preceding computations for one wing only, while hundreds of hours would be required if all the weights were included. With the aid of the formulas derived in the present paper, the preceding work can be performed with a degree of accuracy sufficient for practical purposes in from one to two hours, the only required data being the geometric dimensions of the outer wing (tapered part), the position of its longerons, the total weight of the outer wing, and the approximate weight of the longerons, The entire material presented in this paper is applicable mainly to wings of longeron construction of the CAHI type and investigations are therefore being conducted by CAHI for the derivation of formulas for the determination of the preceding data for wings of other types.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1052 , Report of the Central Aero-Hydrodynamical Institute, Moscow; Rept-452
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 88
    facet.materialart.
    Unknown
    Heat Transfer of Airfoils and Plates (1943)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The few available test data on the heat dissipation of wholly or partly heated airfoil models are compared with the corresponding data for the flat plate as obtained by an extension of Prandtl's momentum theory, with differentiation between laminar and turbulent boundary layer and transitional region between both, the extent and appearance of which depend upon certain critical factors. The satisfactory agreement obtained justifies far-reaching conclusions in respect to other profile forms and arrangements of heated surface areas. The temperature relationship of the material quantities in its effect on the heat dissipation is discussed as far as is possible at tk.e present state of research, and it is shown that the profile drag of heated wing surfaces can increase or decrease with the temperature increase depending upon the momentarily existent structure of the boundary layer.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1044 , Jahrbuch 1938 der Deutschen Luftfahrtforschung; 245-256
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 89
    facet.materialart.
    Unknown
    Tests of a Northrop XSSM-A-3 Missile in the Ames 40- by 80-Foot Wind Tunnel: Stability and Control (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: This report presents the results of wind-tunnel force tests which were conducted to determine the low-speed stability and control characteristics of a full-scale Northrop XSSM-A-3 missile. Tests were made through a range of angles of attack, sideslip, and control deflection, and at various Reynolds numbers. Characteristics of the complete missile are compared with the characteristics of the missile with the landing skids extended, with the vertical tail removed, and with the fuselage alone. No analysis of the data has been made in order to make the results available as soon as possible.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SA50D05
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 90
    facet.materialart.
    Unknown
    An Investigation of the Effects of a Vortex-Generator Configuration on the Aerodynamic Characteristics of a 1/4-Scale Model of the X-1 Airplane (10-Percent-Thick Wing) (1952)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation of a vortex-generator configuration on the wings of a l/4-scale model of the X-1 airplane having a 10-percent-thick wing was conducted in the Langley 16-foot transonic tunnel. The effect of the vortex generators was determined by comparing the model aerodynamic characteristics, wing-pressure distributions, and wing-wake patterns for model configurations with and without vortex generators on the wings. Results are presented from tests at 0.1 increments in Mach number from about 0.69 to 0.99, at Reynolds numbers of about 4.1 x 10(exp 6) to 4.7 x 10(exp 6), and through an angle-of-attack range up to 1.5 deg at lower speeds and up to 5 deg at the highest speed. In general, little difference in the aerodynamic characteristics was observed, except at a Mach number of 0.90 where a rearward movement of the shock on the upper surface of the wing with the vortex generators installed resulted in less separation.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-L52L26
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 91
    facet.materialart.
    Unknown
    The Zero-Lift Drag of Several Configurations of the XAAM-N-2 Pilotless Aircraft. TED No. NACA DE332 (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Free-flight tests have been made to determine the zero-lift drag of several configurations of the XAAM-N-2 pilotless aircraft. Base-pressure measurements were also obtained for some of the configurations. The results show that increasing the wing-thickness ratio from 4 to 6 percent increased the wing drag by about 100 percent at M = 1.3 and by about 30 percent at M = 1.8. Increasing the nose fineness ratio from 5.00 to 6.25 reduced the drag coefficient of the wingless models a maximum of about 0.030 (10 percent) at M = 2.0. A corresponding change in nose shape for the winged models decreased the drag coefficient by about 0.05 in the Mach number range from 1.1 to 1.4; at Mach numbers greater than 1.6 no measurable reduction in drag coefficient was obtained. The drag of the present Sparrow fuselage is less than that of a parabolic fuselage which could contain the same equipment.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL50C16a
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 92
    facet.materialart.
    Unknown
    A Brief Hydrodynamic Investigation of a 1/24-Scale Model of the DR-77 Seaplane (1953)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A limited investigation of a 1/24-scale dynamically similar model of the Navy Bureau of Aeronautics DR-77 design was conducted in Langley tank no. 2 to determine the calm-water take-off and the rough-water landing characteristics of the design with particular regard to the take-off resistance and the landing accelerations. During the take-off tests, resistance, trim, and rise were measured and photographs were taken to study spray. During the landing tests, motion-picture records and normal-acceleration records were obtained. A ratio of gross load to maximum resistance of 3.2 was obtained with a 30 deg. dead-rise hydro-ski installation. The maximum normal accelerations obtained with a 30 deg. dead-rise hydro-ski installation were of the order of 8g to log in waves 8 feet high (full scale). A yawing instability that occurred just prior to hydro-ski emergence was improved by adding an afterbody extension, but adding the extension reduced the ratio of gross load to maximum resistance to 2.9.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL53F04
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 93
    facet.materialart.
    Unknown
    Effect of Various Blade Modifications on Performance of a 16-Stage Axial-Flow Compressor. II - Effect on Over-All Performance Characteristics of Increasing Twelfth through Fifteenth Stage Stator-Blade Angles 3 deg (1952)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The stator-blade angles in the twelfth through fifteenth stages of a 16-stage axial-flow compressor were increased 3O. The over-all performance of this modified compressor is compared to the performance of the compressor with original blade angles. The matching characteristics of the modified compressor and a two-stage turbine were obtained and compared to those of the compressor with original blade angles and the same turbine.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E52A10
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 94
    facet.materialart.
    Unknown
    Measurement of the Static Stability and Control and the Damping Derivatives of a 0.13-Scale Model of the Convair XFY-1 Airplane, TED No. NACA DE 368 (1954)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation has been conducted to determine the static stability and control and damping in roll and yaw of a 0.13-scale model of the Convair XFY-1 airplane with propellers off from 0 deg to 90 deg angle of attack. The tests showed that a slightly unstable pitch-up tendency occurred simultaneously with a break in the normal-force curve in the angle-of-attack range from about 27 deg to 36 deg. The top vertical tail contributed positive values of static directional stability and effective dihedral up to an angle of attack of about 35 deg. The bottom tail contributed positive values of static directional stability but negative values of effective dihedral throughout the angle-of-attack range. Effectiveness of the control surfaces decreased to very low values at the high angles of attack, The model had positive damping in yaw and damping in roll about the body axes over the angle-of-attack range but the damping in yaw decreased to about zero at 90 deg angle of attack.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL54J04
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 95
    facet.materialart.
    Unknown
    Preliminary Altitude Performance Data for the J65-B3 Turbojet Engine at Reynolds Number Indices from 0.2 to 0.8 (1954)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Altitude performance characteristics of the J65-B3 turbojet engine and its components were obtained at engine-inlet conditions corresponding to Reynolds number indices from 0.2 to 0.8 over a range of corrected engine speeds from 70 to 110 percent of rated speed. Engine operational limits up to an altitude of 75,000 feet together with ignition and windmilling characteristics were also obtained. The engine and component data are presented both in graphical and in tabulated form. The operational characteristics are presented in graphical form.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SE54H18
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 96
    facet.materialart.
    Unknown
    Contribution to the Design of Plywood Shells (1942)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The writer sets out to prove by calculation and experiment that by extensive utilization of the skin to carry axial load (reduction of stringer spacing) the stringer sections can be made small enough to afford a substantial saving in structural weight. This saving ranges from 5 to about 40 percent.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1031 , Luftfahrtforschung; 18; 9; 331-337
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 97
    facet.materialart.
    Unknown
    Hydrodynamic Properties of Planing Surfaces and Flying Boats (1950)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The study of the hydrodynamic properties of planing bottom of flying boats and seaplane floats is at the present time based exclusively on the curves of towing tests conducted in tanks. In order to provide a rational basis for the test procedure in tanks and practical design data, a theoretical study must be made of the flow at the step and relations derived that show not only qualitatively but quantitatively the inter-relations of the various factors involved. The general solution of the problem of the development of hydrodynamic forces during the motion of the seaplane float or flying boat is very difficult for it is necessary to give a three-dimensional solution, which does not always permit reducing the analysis to the form of workable computation formulas. On the other had, the problem is complicated by the fact that the object of the analysis is concerned with two fluid mediums, namely, air and water, which have a surface of density discontinuity between them. The theoretical and experimental investigations on the hydrodynamics of a ship cannot be completely carried over to the design of floats and flying-boat hulls, because of the difference in the shape of the contour lines of the bodies, and, because of the entirely different flow conditions from the hydrodynamic viewpoint.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1246 , Materialy po Gidrodinamicheskomu Raschetu Glisserov i Gidrosamoletov; 1-39; CAHI-Rept-149
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 98
    facet.materialart.
    Unknown
    Wind-Tunnel Procedure for Determination of Critical Stability and Control Characteristics of Airplanes (1944)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: This report outlines the flight conditions that are usually critical in determining the design of components of an airplane which affect its stability and control characteristics. The wind-tunnel tests necessary to determine the pertinent data for these conditions are indicated, and the methods of computation used to translate these data into characteristics which define the flying qualities of the airplane are illustrated.
    Keywords: Aircraft Stability and Control
    Type: NACA/TR-781
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 99
    facet.materialart.
    Unknown
    An Interim Report on the Stability and Control of Tailless Airplanes (1944)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Problems relating to the stability and control of tailless airplanes are discussed in consideration of contemporary experience and practice.
    Keywords: Aircraft Stability and Control
    Type: NACA/TR-796
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 100
    facet.materialart.
    Unknown
    Flight Studies of the Horizontal-Tail Loads Experienced by a Fighter Airplane in Abrupt Maneuvers (1944)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Field measurements were made on a fighter airplane to determine the approximate magnitude of the horizontal tail loads in accelerated flight. In these flight measurements, pressures at a few points were used as an index of the tail loads by correlating these pressures with complete pressure-distribution data obtained in the NACA full-scale tunnel. In addition, strain gages and motion pictures of tail deflections were used to explore the general nature and order of magnitude of fluctuating tail loads in accelerated stalls.
    Keywords: Aircraft Stability and Control
    Type: NACA/TR-792
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
Close ⊗
This website uses cookies and the analysis tool Matomo. More information can be found here...