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  • 42.75
  • Aircraft Design, Testing and Performance
  • Aircraft Propulsion and Power
  • Temperatur
  • 1990-1994  (87)
  • 1950-1954  (129)
Collection
Keywords
Publisher
Years
Year
  • 1
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    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
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  • 2
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    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
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  • 3
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    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
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  • 4
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    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
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  • 5
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    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
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  • 6
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    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
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  • 7
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    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
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  • 8
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    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
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  • 9
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    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
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  • 10
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    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
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  • 11
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    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
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  • 12
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    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
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  • 13
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    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
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  • 14
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    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
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  • 15
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    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
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  • 16
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    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
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  • 17
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    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
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  • 18
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    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
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  • 19
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    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
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  • 20
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    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
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  • 21
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    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
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    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
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    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
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  • 24
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    Flight Research Using F100 Engine P680063 in the NASA F-15 Airplane (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The value of flight research in developing and evaluating gas turbine engines is high. NASA Dryden Flight Research Center has been conducting flight research on propulsion systems for many years. The F100 engine has been tested in the NASA F-15 research airplane in the last three decades. One engine in particular, S/N P680063, has been used for the entire program and has been flown in many pioneering propulsion flight research activities. Included are detailed flight-to-ground facility tests; tests of the first production digital engine control system, the first active stall margin control system, the first performance-seeking control system; and the first use of computer-controlled engine thrust for emergency flight control. The flight research has been supplemented with altitude facility tests at key times. This paper presents a review of the tests of engine P680063, the F-15 airplanes in which it flew, and the role of the flight test in maturing propulsion technology.
    Keywords: Aircraft Propulsion and Power
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    IMAGE: A Design Integration Framework Applied to the High Speed Civil Transport (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Effective design of the High Speed Civil Transport requires the systematic application of design resources throughout a product's life-cycle. Information obtained from the use of these resources is used for the decision-making processes of Concurrent Engineering. Integrated computing environments facilitate the acquisition, organization, and use of required information. State-of-the-art computing technologies provide the basis for the Intelligent Multi-disciplinary Aircraft Generation Environment (IMAGE) described in this paper. IMAGE builds upon existing agent technologies by adding a new component called a model. With the addition of a model, the agent can provide accountable resource utilization in the presence of increasing design fidelity. The development of a zeroth-order agent is used to illustrate agent fundamentals. Using a CATIA(TM)-based agent from previous work, a High Speed Civil Transport visualization system linking CATIA, FLOPS, and ASTROS will be shown. These examples illustrate the important role of the agent technologies used to implement IMAGE, and together they demonstrate that IMAGE can provide an integrated computing environment for the design of the High Speed Civil Transport.
    Keywords: Aircraft Design, Testing and Performance
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    Lightplane Wing Design (1992)
    In:  CASI
    Details
    Publication Date: 2018-06-09
    Description: Venture, a kit airplane designed and manufactured by Questair, is a high performance lightplane with excellent low speed characteristics and enhanced safety due to NASA technology incorporated in its unusual wing design. In 1987, North Carolina State graduate students and Langley Research Center spent seven months researching and analyzing the Venture. The result was a wing modification, improving control and providing more usable lift. The plane subsequently set 10 world speed records.
    Keywords: Aircraft Design, Testing and Performance
    Type: Spinoff 1992; 59; NASA-NP-201
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    Business Jet (1991)
    In:  CASI
    Details
    Publication Date: 2018-06-09
    Description: The Citation Jet, developed by Cessna Aircraft Company, Wichita, KS, is the first business jet to employ Langley Research Center's natural laminar flow (NLF) technology. NLF reduces drag and therefore saves fuel by using only the shape of the wing to keep the airflow smooth, or laminar. This reduces friction between the air and wing, and therefore, reduces drag. NASA's Central Industrial Applications Center, Rural Enterprises, Inc., Durant, OK, its Kansas affiliate, and Wichita State University assisted in the technology transfer.
    Keywords: Aircraft Design, Testing and Performance
    Type: Spinoff 1991; 72; NASA-NP-147
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  • 28
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    Small Business Innovations (Helicopters) (1992)
    In:  CASI
    Details
    Publication Date: 2018-06-09
    Description: The amount of engine power required for a helicopter to hover is an important, but difficult, consideration in helicopter design. The EHPIC program model produces converged, freely distorted wake geometries that generate accurate analysis of wake-induced downwash, allowing good predictions of rotor thrust and power requirements. Continuum Dynamics, Inc., the Small Business Innovation Research (SBIR) company that developed EHPIC, also produces RotorCRAFT, a program for analysis of aerodynamic loading of helicopter blades in forward flight. Both helicopter codes have been licensed to commercial manufacturers.
    Keywords: Aircraft Design, Testing and Performance
    Type: Spinoff 1992; 122-125; NASA-NP-201
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  • 29
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    Helicopter Strakes (1993)
    In:  CASI
    Details
    Publication Date: 2018-06-09
    Description: Langley Research Center has done extensive research into the effectiveness of tail boom strakes on conventional tail rotor helicopters. (A strake is a "spoiler" whose purpose is to alter the airflow around an aerodynamic body.) By placing strakes on a tail boom, the air loading can be changed, thrust and power requirements of the tail rotor can be reduced, and helicopter low speed flight handling qualities are improved. This research led to the incorporation of tail boom strakes on three production-type commercial helicopters manufactured by McDonnell Douglas Helicopter Company.
    Keywords: Aircraft Design, Testing and Performance
    Type: Spinoff 1993; 92-93; NASA-NP-211
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    Winglets for the Airlines (1994)
    In:  CASI
    Details
    Publication Date: 2018-06-09
    Description: Originally developed as part of the Aircraft Energy Efficiency Program in the 1970's, winglets are now used by long-ranging aircraft as well as business jets and smaller planes. The winglet is an upturned wingtip, a lifting surface designed to operate in the wingtip "vortex," a whirlpool of air at an airplane's wingtips. It takes advantage of the turbulent vortex flow by producing forward thrust. This reduces drag and improves fuel efficiency. After McDonnell Douglas conducted wind tunnel tests of winglets in 1978-79, the technology was incorporated into the MD-11, their large payload, long range airplane. There are now more than 100 MD-11s in service.
    Keywords: Aircraft Design, Testing and Performance
    Type: Spinoff 1994; 90-91; NASA-NP-214
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    Optimum Design of High-Speed Prop-Rotors (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An integrated multidisciplinary optimization procedure is developed for application to rotary wing aircraft design. The necessary disciplines such as dynamics, aerodynamics, aeroelasticity, and structures are coupled within a closed-loop optimization process. The procedure developed is applied to address two different problems. The first problem considers the optimization of a helicopter rotor blade and the second problem addresses the optimum design of a high-speed tilting proprotor. In the helicopter blade problem, the objective is to reduce the critical vibratory shear forces and moments at the blade root, without degrading rotor aerodynamic performance and aeroelastic stability. In the case of the high-speed proprotor, the goal is to maximize the propulsive efficiency in high-speed cruise without deteriorating the aeroelastic stability in cruise and the aerodynamic performance in hover. The problems studied involve multiple design objectives; therefore, the optimization problems are formulated using multiobjective design procedures. A comprehensive helicopter analysis code is used for the rotary wing aerodynamic, dynamic and aeroelastic stability analyses and an algorithm developed specifically for these purposes is used for the structural analysis. A nonlinear programming technique coupled with an approximate analysis procedure is used to perform the optimization. The optimum blade designs obtained in each case are compared to corresponding reference designs.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-CR-204285 , NAS 1.26:204285
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  • 32
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    Detection of Fatigue Cracks at Rivets with Self-Nulling Probe (1994)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: A new eddy current probe developed at NASA Langley Research Center has been used to detect small cracks at rivets in aircraft lap splices [1]. The device has earlier been used to detect isolated fatigue cracks with a minimum detectable flaw size of roughly 1/2 to 1/3 the diameter of the probe [2]. The present work shows that the detectable flaw size for cracks originating at rivets can be greatly improved upon from that of isolated flaws. The use of a rotating probe method combined with spatial filtering has been used to detect 0.18 cm EDM notches, as measured from the rivet shank, with a 1.27 cm diameter probe and to detect flaws buried under the rivet head, down to a length of 0.076 cm, using a 0.32 cm diameter probe. The Self-Nulling Electromagnetic Flaw Detector induces a high density eddy current ring in the sample under test. A ferromagnetic flux focusing lens is incorporated such that in the absence of any inhomogeneities in the material under test only a minimal magnetic field will reach the interior of the probe. A magnetometer (pickup coil) located in the center of the probe therefore registers a null voltage in the absence of material defects. When a fatigue crack or other discontinuity is present in the test article the path of the eddy currents in the material is changed. The magnetic field associated with these eddy currents then enter into the interior of the probe, producing a large output voltage across the pickup coil leads. Further
    Keywords: Aircraft Design, Testing and Performance
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    Flight Dynamics and Control of Elastic Hypersonic Vehicles Uncertainty Modeling (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: It has been shown previously that hypersonic air-breathing aircraft exhibit strong aeroelastic/aeropropulsive dynamic interactions. To investigate these, especially from the perspective of the vehicle dynamics and control, analytical expressions for key stability derivatives were derived, and an analysis of the dynamics was performed. In this paper, the important issue of model uncertainty, and the appropriate forms for representing this uncertainty, is addressed. It is shown that the methods suggested in the literature for analyzing the robustness of multivariable feedback systems, which as a prerequisite to their application assume particular forms of model uncertainty, can be difficult to apply on real atmospheric flight vehicles. Also, the extent to which available methods are conservative is demonstrated for this class of vehicle dynamics.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-CR-202600 , NAS 1.26:202600 , AIAA Paper 94-3629
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    Free Flight Rotorcraft Flight Test Vehicle Technology Development (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A rotary wing, unmanned air vehicle (UAV) is being developed as a research tool at the NASA Langley Research Center by the U.S. Army and NASA. This development program is intended to provide the rotorcraft research community an intermediate step between rotorcraft wind tunnel testing and full scale manned flight testing. The technologies under development for this vehicle are: adaptive electronic flight control systems incorporating artificial intelligence (AI) techniques, small-light weight sophisticated sensors, advanced telepresence-telerobotics systems and rotary wing UAV operational procedures. This paper briefly describes the system's requirements and the techniques used to integrate the various technologies to meet these requirements. The paper also discusses the status of the development effort. In addition to the original aeromechanics research mission, the technology development effort has generated a great deal of interest in the UAV community for related spin-off applications, as briefly described at the end of the paper. In some cases the technologies under development in the free flight program are critical to the ability to perform some applications.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-111571 , NAS 1.15:111571
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    Effects of Mistuning on the Forced Response of Turbomachinery Rotors (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The basic purpose of this research has been to develop a fundamental understanding of the effects of blade-to-blade dissimilarities, or mistuning, on the dynamics of nearly cyclic bladed-disk assemblies. This topic is of importance as mistuning has been shown to increase the forced response amplitudes of some blades significantly, and even to lead to blade failure. Furthermore, the current trend toward high performance propulsion turbomachinery designed for finite service life demands an accurate prediction of system performance and dynamics at the design stage. This objective has been achieved by carrying out the following tasks. First, the investigation of the free and forced responses of representative, yet sufficiently simple blade assembly models that capture all the important characteristics of typical turbomachinery rotors. Second, the development of computational methods that predict the effects of mistuning in a systematic and reliable way, along with the development of a systematic reduced-order modeling procedure for mistuned bladed disks. Third, the application of these findings and the tools developed to an industrial rotor, namely the first stage of turbine blades of the oxidizer turbopump in the space shuttle main rocket engine (SSME). The research supported by NASA has led to the development of a coherent theory for mistuned blade assemblies. The further implementation of these computational tools into the forced response prediction system currently under development in the Structural Dynamics Branch-FREPS-would enable the designer and the analyst to: (1) identify types of blade assemblies highly sensitive to mistuning in various frequency and other parameter ranges and (2) characterize mistuning effects on their forced response by predicting true response amplitudes and fatigue life estimates.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-CR-205484 , NAS 1.26:205484
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    Improved Finite Element Modeling of the Turbofan Engine Inlet Radiation Problem (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Improvements have been made in the finite element model of the acoustic radiated field from a turbofan engine inlet in the presence of a mean flow. The problem of acoustic radiation from a turbofan engine inlet is difficult to model numerically because of the large domain and high frequencies involved. A numerical model with conventional finite elements in the near field and wave envelope elements in the far field has been constructed. By employing an irrotational mean flow assumption, both the mean flow and the acoustic perturbation problem have been posed in an axisymmetric formulation in terms of the velocity potential; thereby minimizing computer storage and time requirements. The finite element mesh has been altered in search of an improved solution. The mean flow problem has been reformulated with new boundary conditions to make it theoretically rigorous. The sound source at the fan face has been modeled as a combination of positive and negative propagating duct eigenfunctions. Therefore, a finite element duct eigenvalue problem has been solved on the fan face and the resulting modal matrix has been used to implement a source boundary condition on the fan face in the acoustic radiation problem. In the post processing of the solution, the acoustic pressure has been evaluated at Gauss points inside the elements and the nodal pressure values have been interpolated from them. This has significantly improved the results. The effect of the geometric position of the transition circle between conventional finite elements and wave envelope elements has been studied and it has been found that the transition can be made nearer to the inlet than previously assumed.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-CR-204341 , NAS 1.26:204341
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    Status of the Validation of High-Angle-Of-Attack Nose-Down Pitch Control Margin Design Guidelines (1992)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: This paper presents a summary of results obtained to date in an ongoing cooperative research program between NASA and the U.S. Navy to develop design criteria for high-angle-of-attack nose- down pitch control for combat aircraft. A fundamental design consideration for aircraft incorporating relaxed static stability in pitch is the level of stability which achieves a proper balance between high- speed performance considerations and low-speed requirements for maneuvering at high angles of attack. A comprehensive data base of piloted simulation results was generated for parametric variations of critical parameters affecting nose-down control capability. The results showed a strong correlation of pilot rating to the short-term pitch response for nose-down commands applied at high- angle-of-attack conditions. Using these data, candidate design guidelines and flight demonstration requirements were defined. Full- scale flight testing to validate the research methodology and proposed guidelines is in progress, some preliminary results of which are reviewed.
    Keywords: Aircraft Design, Testing and Performance
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    Comparison of High-Speed Operating Characteristics of Size 215 Cylindrical-Roller Bearings as Determined in Turbojet Engine and in Laboratory Test Rig (1951)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A comparison of the operating characteristics of 75-millimeter-bore (size 215) cylindrical-roller one-piece inner-race-riding cage-type bearings was made using a laboratory test rig and a turbojet engine. Cooling correlation parameters were determined by means of dimensional analysis, and the generalized results for both the inner- and outer-race bearing operating temperatures are compared for the laboratory test rig and the turbojet engine. Inner- and outer-race cooling-correlation curves were obtained for the turbojet-engine turbine-roller bearing with the same inner- and outer-race correlation parameters and exponents as those determined for the laboratory test-rig bearing. The inner- and outer-race turbine roller-bearing temperatures may be predicted from a single curve, regardless of variations in speed, load, oil flow, oil inlet temperature, oil inlet viscosity, oil-jet diameter or any combination of these parameters. The turbojet-engine turbine-roller-bearing inner-race temperatures were 30 to 60 F greater than the outer-race-maximum temperatures, the exact values depending on the operating condition and oil viscosity; these results are in contrast to the laboratory test-rig results where the inner-race temperatures were less than the outer-race-maximum temperatures. The turbojet-engine turbine-roller bearing, maximum outer-race circumferential temperature variation was approximately 30 F for each of the oils used. The effect of oil viscosity on inner- and outer-race turbojet-engine turbine-roller-bearing temperatures was found to be significant. With the lower viscosity oil (6x10(exp -7) reyns (4.9 centistokes) at 100 F; viscosity index, 83), the inner-race temperature was approximately 30 to 35 F less than with the higher viscosity oil (53x10(exp -7) reyns (42.8 centistokes) at 100 F; viscosity index, 150); whereas the outer-race-maximum temperatures were 12 to 28 F lower with the lower viscosity oil over the DN range investigated.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E51I05
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  • 39
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    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
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    Accuracy of Tilt Rotor Hover Performance Predictions (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The accuracy of various methods used to predict tilt rotor hover performance was established by comparing predictions with large-scale experimental data. A wide range of analytical approaches were examined. Blade lift was predicted with a lifting line analysis, two lifting surface analyses, and by a finite-difference solution of the full potential equation. Blade profile drag was predicted with two different types of airfoil tables and an integral boundary layer analysis. The inflow at the rotor was predicted using momentum theory, two types of prescribed wakes, and two free wake analyses. All of the analyses were accurate at moderate thrust coefficients. The accuracy of the analyses at high thrust coefficients was dependent upon their treatment of high sectional angles of attack on the inboard sections of the rotor blade. The analyses which allowed sectional lift coefficients on the inboard stations of the blade to exceed the maximum observed in two-dimensional wind tunnel tests provided better accuracy at high thrust coefficients than those which limited lift to the maximum two-dimensional value. These results provide tilt rotor aircraft designers guidance on which analytical approaches provide the best results, and the level of accuracy which can be expected from the best analyses.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-104023 , A-93083 , NAS 1.15:104023 , ARC-E-DAA-TN27262
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    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
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  • 42
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    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
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    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
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  • 44
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    Relation Between Inflammables and Ignition Sources in Aircraft Environments (1950)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A literature survey was conducted to determine the relation between aircraft ignition sources and inflammables. Available literature applicable to the problem of aircraft fire hazards is analyzed and, discussed herein. Data pertaining to the effect of many variables on ignition temperatures, minimum ignition pressures, and minimum spark-ignition energies of inflammables, quenching distances of electrode configurations, and size of openings incapable of flame propagation are presented and discussed. The ignition temperatures and the limits of inflammability of gasoline in air in different test environments, and the minimum ignition pressure and the minimum size of openings for flame propagation of gasoline - air mixtures are included. Inerting of gasoline - air mixtures is discussed.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TN-2227
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  • 45
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    Tests of Two-Blade Propellers in the Langley 8-Foot High-Speed Tunnel to Determine the Effect on Propeller Performance of a Modification of Inboard Pitch Distribution (1951)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests of two propellers having two blades and differing only in the inboard pitch distribution were made in the Langley 8-foot highspeed tunnel to determine the effect of inboard pitch distribution on propeller performance. propeller was designed for operation in the reduced velocity region ahead of an NACA cowling; the inboard pitch distribution of the modified propeller was increased for operation at or near free-stream velocities, such as would be obtained in a pusher installation. conditions covering climb, cruise, and high-speed operation. Wake surveys were taken behind the propellers in order to determine the distribution of thrust along the blades and to aid in the analysis of the results. Test results showed that the modified propeller was about 2.5 percent less efficient for a typical climb condition at all altitudes, 2 percent more efficient for one cruise condition, and 5 percent more efficient for high-speed operation. speed condition, the modified propeller showed a 6-percent loss in efficiency due to compressibility; whereas the original propeller showed an 11-percent efficiency loss due to compressiblity. The lower compressibility loss for the modified propeller resulted from the fact that the inboard sections of this propeller could operate at increased thrust loading after compressibility losses had occurred at the outboard sections.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TN-2268
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  • 46
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    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
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  • 47
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    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
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  • 48
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    Investigation of the NACA 4-(3)(8)-045 Two-blade Propellers at Forward Mach Numbers to 0.725 to Determine the Effects of Compressibility and Solidity on Performance (1950)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As part of a general investigation of propellers at high forward speeds, tests of two 2-blade propellers having the NACA 4-(3)(8)-03 and NACA 4-(3)(8)-45 blade designs have been made in the Langley 8-foot high-speed tunnel through a range of blade angle from 20 degrees to 60 degrees for forward Mach numbers from 0.165 to 0.725 to establish in detail the changes in propeller characteristics due to compressibility effects. These propellers differed primarily only in blade solidity, one propeller having 50 percent and more solidity than the other. Serious losses in propeller efficiency were found as the propeller tip Mach number exceeded 0.91, irrespective of forward speed or blade angle. The magnitude of the efficiency losses varied from 9 percent to 22 percent per 0.1 increase in tip Mach number above the critical value. The range of advance ratio for peak efficiency decreased markedly with increase of forward speed. The general form of the changes in thrust and power coefficients was found to be similar to the changes in airfoil lift coefficient with changes in Mach number. Efficiency losses due to compressibility effects decreased with increase of blade width. The results indicated that the high level of propeller efficiency obtained at low speeds could be maintained to forward sea-level speeds exceeding 500 miles per hour.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TR-999
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  • 49
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    The Supersonic Axial-Flow Compressor (1950)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation has been made to explore the possibilities of axial-flow compressors operating with supersonic velocities into the blade rows. Preliminary calculations showed that very high pressure ratios across a stage, together with somewhat increased mass flows, were apparently possible with compressors which decelerated air through the speed of sound in their blading. The first phase of the investigation was the development of efficient supersonic diffusers to decelerate air through the speed of sound. The present report is largely a general discussion of some of the essential aerodynamics of single-stage supersonic axial-flow compressors. As an approach to the study of supersonic compressors, three possible velocity diagrams are discussed briefly. Because of the encouraging results of this study, an experimental single-stage supersonic compressor has been constructed and tested in Freon-12. In this compressor, air decelerates through the speed of sound in the rotor blading and enters the stators at subsonic speeds. A pressure ratio of about 1.8 at an efficiency of about 80 percent has been obtained.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TR-974 , NACA-ACR-L6D02 , NACA-AR-36
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  • 50
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    Investigation of Noise Field and Velocity Profiles of an Afterburning Engine (1954)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Sound pressure levels, frequency spectrum, and jet velocity profiles are presented for an engine-afterburner combination at various values of afterburner fuel - air ratio. At the high fuel-air ratios, severe low-frequency resonance was encountered which represented more than half the total energy in the sound spectrum. At similar thrust conditions, lower sound pressure levels were obtained from a current fighter air craft with a different afterburner configuration. The lower sound pressure levels are attributed to resonance-free afterburner operation and thereby indicate the importance of acoustic considerations in afterburner design.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E54G07
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  • 51
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    Flutter Clearance of the F-14A Variable-Sweep Transition Flight Experiment Airplane, Phase 2 (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An F-14A aircraft was modified for use as the test-bed aircraft for the variable-sweep transition flight experiment (VSTFE) program. The VSTFE program was a laminar flow research program designed to measure the effects of wing sweep on laminar flow. The airplane was modified by adding an upper surface foam and fiberglass glove to the right wing. An existing left wing glove had been added for the previous phase of the program. Ground vibration and flight flutter testing were accomplished to verify the absence of aeroelastic instabilities within a flight envelope of Mach 0.9 or 450 knots, calibrated airspeed, whichever was less. Flight test data indicated satisfactory damping levels and trends for the elastic structural modes of the airplane. Ground vibration test data are presented along with in-flight frequency and damping estimates, time histories and power spectral densities of in-flight sensors, and pressure distribution data.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-101717 , H-1598 , NAS 1.15:101717
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  • 52
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    Review of Full-Scale F/A-18 Research at NASA Ames Research Center (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: Results of flow visualization and tail buffett studies conducted on a full-scale production F/A-18 fighter aircraft in the 80- by 120-Foot Wind Tunnel of the National Full-Scale Aerodynamic Complex are presented. Test conditions range between 20 degrees and 40 degrees angle of attack, 16 degrees and -16 degrees side-slip angle, and up to a Mach number of 0.15 (corresponding to a Reynolds number of 12.3 x 10(exp 6) based on mean aerodynamic chord). Flow visualization results include both surface and off-surface techniques that examine forebody, canopy, leading-edge extension, and wing flow fields. Unsteady pressures measured at 96 locations on the port tail fin are used to determine the effect of a removable leading-edge extension fence on tail buffet loads at high angle of attack. Analyses and comparisons include tail fin bending moment and wave velocities on the tail surface. Repeatability and scaling issues are assessed through comparison with measurements from previous full-scale tests and several small-scales tests.
    Keywords: Aircraft Design, Testing and Performance
    Type: May 24, 1994 - May 26, 1994; Ottawa; Canada|May 31, 1994; Medley, Alberta; Canada
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  • 53
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    Sonic and Supersonic Jet Plumes (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: Study of sonic and supersonic jet plumes are relevant to understanding such phenomenon as jet-noise, plume signatures, and rocket base-heating and radiation. Jet plumes are simple to simulate and yet, have complex flow structures such as Mach disks, triple points, shear-layers, barrel shocks, shock- shear- layer interaction, etc. Experimental and computational simulation of sonic and supersonic jet plumes have been performed for under- and over-expanded, axisymmetric plume conditions. The computational simulation compare very well with the experimental observations of schlieren pictures. Experimental data such as temperature measurements with hot-wire probes are yet to be measured and will be compared with computed values. Extensive analysis of the computational simulations presents a clear picture of how the complex flow structure develops and the conditions under which self-similar flow structures evolve. From the computations, the plume structure can be further classified into many sub-groups. In the proposed paper, detail results from the experimental and computational simulations for single, axisymmetric, under- and over-expanded, sonic and supersonic plumes will be compared and the fluid dynamic aspects of flow structures will be discussed.
    Keywords: Aircraft Design, Testing and Performance
    Type: 29th AIAA Thermophysics Conference; Jun 19, 1995 - Jun 22, 1995; San Diego, CA; United States
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  • 54
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    Maneuver Performance Enhancement for an Advanced Fighter/Attack Aircraft (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: A small scale wind tunnel test of a realistic fighter configuration has been completed in NASA Ames' 7'x10' wind tunnel. This test was part of the Fighter Lift and Control (FLAC) program, a joint NASA - USAF research program, involving small and large-scale wind-tunnel tests and computational analysis of unique lift augmentation and control devices. The goal of this program is to enhance the maneuver and control capability of next-generation Air Force multi-role fighter aircraft with low-observables geometries. The principal objective of this test was to determine the effectiveness of passive boundary layer control devices at increasing L/D at sustained maneuver lift coefficients. Vortex generators (VGs) were used to energize the boundary layer to prevent or delay separation. Corotating vanes, counter-rotating vanes, and Wheeler Wishbone VGs were used in the vicinity of the leading and trailing edge flap hinge lines. Principle test parameters were leading and trailing edge flap deflections, and location, size, spacing, and orientation for each VG type. Gurney flaps were also tested. Data gathered include balance force and moment data, surface pressures, and flow visualization for characterizing flow behavior and locating separation lines. Results were quite different for the two best flap configurations tested. All VG types tested showed improvement (up to 5%) in maneuver L/D with flaps at LE=20 degrees, TE=0 degrees. The same VGs degraded performance, in all but a few cases, with flaps at LE=15 degrees, TE=10 degrees.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Aerospace Atlantic; Apr 19, 1994 - Apr 21, 1994; Dayton, OH; United States
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  • 55
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    Computational Investigation of an F-18 Aircraft in the High-Alpha Regime (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: One of the goals of NASA's High Alpha Technology Program is to provide flight-validated design methods for the high-angle-of-attack regime. This is an integrated effort utilizing computational simulations, wind tunnel experiments, and flight tests using the F-18 High Alpha Research Vehicle (HARV). The dominant physics of the aircraft flows in the high alpha regime changes as the angle of attack is increased. At moderate angle of attack the flow is characterized by boundary layer separation and the formation of tight vortices. As the angle of attack is increased, these vortices break down producing unsteady wakes. With further increase in angle of attack, the, vortex breakdown moves progressively upstream until the entire flowfield becomes dominated by the unsteady wake. Previous computational work has demonstrated the ability to simulate flows about the F-18 HARV in the medium-to-high angle of attack range, where the flowfield is characterized by the vortex formation and subsequent breakdown. This paper extends the previous computations to include conditions of 45 degree angle of attack where the flowfield becomes dominated by the unsteady wake shed from the Leading Edge Extension (LEX), and regions of laminar and transitional flow appear on the fuselage forebody. A more complete surface geometry is utilized, which includes the features of the engine nacelle, inlet diffuser, and the boundary layer diverter duct. A volume grid sensitivity study was also performed to extend the accuracy of the results, most notably in the prediction of the LEX vortex breakdown position. This paper includes comparisons of computational results with both in-flight surface pressure measurements, and flow visualizations of the surface and off-surface particle trajectories.
    Keywords: Aircraft Design, Testing and Performance
    Type: 4th NASA High Alpha Conference/Workshop; Jul 12, 1994 - Jul 14, 1994; Edwards, CA; United States
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  • 56
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    In Operation Detection and Correction of Rotor Imbalance in Jet Engines Using Active Vibration Control (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Jet Engines may experience severe vibration due to the sudden imbalance caused by blade failure. This research investigates employment of on board magnetic bearings or piezoelectric actuators to cancel these forces in flight. This operation requires identification of the source of the vibrations via an expert system, determination of the required phase angles and amplitudes for the correction forces, and application of the desired control signals to the magnetic bearings or piezo electric actuators. This paper will show the architecture of the software system, details of the control algorithm used for the sudden imbalance correction project described above, and the laboratory test results.
    Keywords: Aircraft Propulsion and Power
    Type: SAE-TP-941151 , (ISSN 0148-7191)|Aerospace Atlantic Conference and Exposition; Apr 18, 1994 - Apr 22, 1994; Dayton, OH; United States
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  • 57
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    Design Challenges Encountered in a Propulsion-Controlled Aircraft Flight Test Program (1994)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The NASA Dryden Flight Research Center conducted flight tests of a propulsion-controlled aircraft system on an F-15 airplane. This system was designed to explore the feasibility of providing safe emergency landing capability using only the engines to provide flight control in the event of a catastrophic loss of conventional flight controls. Control laws were designed to control the flightpath and bank angle using only commands to the throttles. Although the program was highly successful, this paper highlights some of the challenges associated with using engine thrust as a control effector. These challenges include slow engine response time, poorly modeled nonlinear engine dynamics, unmodeled inlet-airframe interactions, and difficulties with ground effect and gust rejection. Flight and simulation data illustrate these difficulties.
    Keywords: Aircraft Design, Testing and Performance
    Type: H-2000 , AIAA Paper 94-3359 , Joint Propulsion; Jun 27, 1994 - Jun 29, 1994; Indianapolis, IN; United States
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  • 58
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    Analytic Sensitivities for Shape Optimization in Equivalent Plate Structural Wing Models (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Equivalent plate modeling techniques based on Ritz analysis with simple polynomials prove to be efficient tools for structural modeling of wings in the preliminary design stage. Accuracy problems are encountered, however, when these models are used to obtain finite difference behavior sensitivities with respect to planform shape. The accuracy problems are associated with the poor numerical conditioning of static and eigenvalue equations. As higher-order polynomials are being used to Improve the analysis itself, the more sensitive is the finite difference derivative to the step size used. This article describes a formulation of wing equivalent plate modeling in which it is simple to obtain analytic, explicit expressions for stiffness and mass matrix elements without the need to perform numerical integration. This formulation leads naturally to analytic expressions for the derivatives of displacements, stresses, and natural frequencies with respect to shape design variables. This article examines the accuracy of finite difference derivatives compared with the analytic derivatives, and shows that In some cases it is impossible to obtain any information of value by finite differences. Analytic sensitivities, in this case, are still sufficiently accurate for design optimization.
    Keywords: Aircraft Design, Testing and Performance
    Type: Journal of Aircraft; 31; 4; 961-969
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  • 59
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    Dynamically Tuned Blade Pitch Links for Vibration Reduction (1994)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A passive vibration reduction device in which the conventional main rotor blade pitch link is replaced by a spring/damper element is investigated using a comprehensive rotorcraft analysis code. A case study is conducted for a modern articulated helicopter main rotor. Correlation of vibratory pitch link loads with wind tunnel test data is satisfactory for lower harmonics. Inclusion of unsteady aerodynamics had little effect on the correlation. In the absence of pushrod damping, reduction in pushrod stiffness from the baseline value had an adverse effect on vibratory hub loads in forward flight. However, pushrod damping in combination with reduced pushrod stiffness resulted in modest improvements in fixed and rotating system hub loads.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-112911 , NAS 1.15:112911 , Annual Forum of the American Helicopter Society; May 11, 1994 - May 13, 1994; Washington, DC; United States
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  • 60
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    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
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  • 61
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    Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine. 7: Rotor-Blade Fabrication Procedures (1951)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was conducted to determine the cooling effectiveness of a wide variety of air-cooled turbine-blade configurations. The blades, which were tested in the turbine of a - commercial turbojet engine that was modified for this investigation by replacing two of the original blades with air-cooled blades located diametrically opposite each other, are untwisted, have no aerodynamic taper, and have essentially the same external profile. The cooling-passage configuration is different for each blade, however. The fabrication procedures were varied and often unique. The blades were fabricated using methods most suitable for obtaining a small number of blades for use in the cooling investigations and therefore not all the fabrication procedures would be directly applicable to production processes, although some of the ideas and steps might be useful. Blade shells were obtained by both casting and forming. The cast shells were either welded to the blade base or cast integrally with the base. The formed shells were attached to the base by a brazing and two welding methods. Additional surface area was supplied in the coolant passages by the addition of fins or tubes that were S-brazed. to the shell. A number of blades with special leading- and trailing-edge designs that provided added cooling to these areas were fabricated. The cooling effectiveness and purposes of the various blade configurations are discussed briefly.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E51E23 , REPT-2203
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  • 62
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    Fluid/Structure Interaction Studies of Aircraft Using High Fidelity Equations on Parallel Computers (1994)
    In:  Other Sources
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    Publication Date: 2019-07-18
    Description: Abstract Aeroelasticity which involves strong coupling of fluids, structures and controls is an important element in designing an aircraft. Computational aeroelasticity using low fidelity methods such as the linear aerodynamic flow equations coupled with the modal structural equations are well advanced. Though these low fidelity approaches are computationally less intensive, they are not adequate for the analysis of modern aircraft such as High Speed Civil Transport (HSCT) and Advanced Subsonic Transport (AST) which can experience complex flow/structure interactions. HSCT can experience vortex induced aeroelastic oscillations whereas AST can experience transonic buffet associated structural oscillations. Both aircraft may experience a dip in the flutter speed at the transonic regime. For accurate aeroelastic computations at these complex fluid/structure interaction situations, high fidelity equations such as the Navier-Stokes for fluids and the finite-elements for structures are needed. Computations using these high fidelity equations require large computational resources both in memory and speed. Current conventional super computers have reached their limitations both in memory and speed. As a result, parallel computers have evolved to overcome the limitations of conventional computers. This paper will address the transition that is taking place in computational aeroelasticity from conventional computers to parallel computers. The paper will address special techniques needed to take advantage of the architecture of new parallel computers. Results will be illustrated from computations made on iPSC/860 and IBM SP2 computer by using ENSAERO code that directly couples the Euler/Navier-Stokes flow equations with high resolution finite-element structural equations.
    Keywords: Aircraft Design, Testing and Performance
    Type: ASME Symposium on Industrial Applications of Parallel Computing; Nov 12, 1995 - Nov 17, 1995; San Francisco, CA; United States
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  • 63
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    Analytical Studies of Prompt NO(x) Emissions from Aircraft Gas Turbine Combustors (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: The reduction of oxides of nitrogen (NO(x)) emissions from aircraft gas turbines is a vital part of the NASA High Speed Research Program (HSRP). Emissions reduction studies are critical to the feasibility of future civil aircraft operating at supersonic speeds in the stratosphere. It is believed that large fleets of supersonic aircraft using conventional gas turbine engines would emit levels of NO(x) that are harmful to the stratospheric ozone layer.
    Keywords: Aircraft Propulsion and Power
    Type: 31st AIAA/SAE/ASME/ASEE Joint Propulsion Conference; Jul 10, 1995 - Jul 12, 1995; San Diego, CA; United States
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  • 64
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    Design of Flight Vehicle Management Systems (1994)
    In:  Other Sources
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    Publication Date: 2019-07-18
    Description: As the operation of large systems becomes ever more dependent on extensive automation, the need for an effective solution to the problem of design and validation of the underlying software becomes more critical. Large systems possess much detailed structure, typically hierarchical, and they are hybrid. Information processing at the top of the hierarchy is by means of formal logic and sentences; on the bottom it is by means of simple scalar differential equations and functions of time; and in the middle it is by an interacting mix of nonlinear multi-axis differential equations and automata, and functions of time and discrete events. The lecture will address the overall problem as it relates to flight vehicle management, describe the middle level, and offer a design approach that is based on Differential Geometry and Discrete Event Dynamic Systems Theory.
    Keywords: Aircraft Design, Testing and Performance
    Type: 33rd IEEE CDC Meeting; Dec 12, 1994 - Dec 14, 1994; Lake Buena Vista, FL; United States
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    Measurements of Forward Flight Effects on the Advanced Ducted Propulsion Demonstrator Engine (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: The performance of the Pratt & Whitney Advanced Ducted Propulsion (ADP) UHB concept has been recently evaluated with studies of a 17 in. diameter fan simulator. Following the model scale tests, a 118 in. diameter demonstrator was tested at the NASA Ames 40- by 80-Foot Wind Tunnel. The 18 blade fan was driven by the low compressor shaft of a PW2037 core through a reduction gear system fabricated by Fiat with approximately 1:3.7 reduction ratio. ne variable pitch fan was hydraulically actuated with settings for take-off, cruise, feather, and reverse thrust. The low-pressure turbine was built by MTU to provide higher shaft power in comparison with the standard PW2037. The demonstrator was provided with 45 vanes located 2.6 fan chords downstream of the rotor, and 10 case struts approximately 1 fan chord downstream of the vanes. The inlet, mid-duct, and exhaust linings were acoustically treated. Acoustic surveys were taken in the for-ward thrust mode for fan speeds of 898, 1120, 1205, and 1302 R.P.M., and at tunnel speeds of 25, 50, 100, and 140 kts. The lowest speed was achieved with the wind tunnel fans at flat pitch, but with the engine pumping the test section Microphone signals were recorded for 30 seconds at 5 deg. increments. These measurements will be used to assess the effects of forward speed on UHB engines, to compare these effects with the corresponding characteristics of conventional bypass ratio engines, and to discuss the various aspects of testing large engines in the wind tunnel.
    Keywords: Aircraft Propulsion and Power
    Type: AIAA/ASME/ASEE Joint Propulsion and Exhibit; Jul 10, 1995 - Jul 12, 1995; San Diego, CA; United States
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    Flight Testing of Hypersonic Airbreathing Propulsion for Developing Computational Design Technology (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: The objective of this paper is to present and discuss a scenario and the requirements for flight testing of hypersonic airbreathing propulsion leading to the development of computational design technology. Flight Testing for this development is a significant part of a triad/synergistic, design approach which integrates computations, flight testing, and ground testing. These three complementary, design developmental tools have various capabilities and limitations. An incremental approach is necessary to use and to develop these tools effectively and efficiently. This computational technology must be developed keeping in focus the aerospace plane that is to be developed. The criteria for selecting the right plane are presented and consequently, the appropriate flight tests are identified. Two conceptual, flight-test systems are suggested considering the following: (1) the relevant, lessons learned from previous and current United States hypersonic programs, from the Apollo program, from the Space Shuttle program, and from the space station program; (2) the current need for a low risk, affordable access to space; and (3) the design challenge for hypersonic airbreathing propulsion testing. How these systems may be used for developing the computational design technology is described. The requirements for conducting propulsion- design computations, sources of uncertainties in these computations, and a guide for establishing the credibility of these computations are also presented.
    Keywords: Aircraft Propulsion and Power
    Type: Second European Symposium on Aerothermodynamics for Space Vehicles; Nov 22, 1994 - Nov 25, 1994; Noordwijk; Netherlands|Fourth European High-Speed Database Workshop; Nov 22, 1994 - Nov 25, 1994; Noordwijk; Netherlands
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  • 67
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    Simulation of Unsteady Combustion in a Ramjet Engine Using a Highly Parallel Computer (1994)
    In:  Other Sources
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    Publication Date: 2019-07-18
    Description: Combustion instability in ramjets is a complex phenomenon that involve nonlinear interaction between acoustic waves, vortex motion and unsteady heat release in the combustor. To numerically simulate this 3-D, transient phenomenon, enormous computer resources (time, memory and disk storage) are required. Although current generation vector supercomputers are capable of providing adequate resources for simulations of this nature, their high cost and limited availability, makes such machines less than satisfactory for routine use. The primary focus of this study is to assess the feasibility of using highly parallel computer systems as a cost-effective alternative for conducting such unsteady flow simulations. Towards this end, a large-eddy simulation model for combustion instability was implemented on the Intel iPSC/860 and a careful study was conducted to determine the benefits and the problems associated with the use of such machines for transient simulations. Details of this study along with the results obtained from the unsteady combustion simulations carried out on the iPSC/860 are discussed in this paper.
    Keywords: Aircraft Propulsion and Power
    Type: 1994 Simulation Multi Conference; Apr 10, 1994 - Apr 15, 1994; San Diego, CA; United States
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  • 68
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    Optimization of Wing-Body Configurations by the Euler Equations (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: This paper describes a new wing-body design procedure which is based on the Euler equations and a constrained numerical optimization technique. The geometry modification is based on a set of fundamental modes defined on the unit interval. A design example involving a generic wing-body model is presented to demonstrate the usefulness of the design program. It is shown that the use of an Euler solver coupled with a direct numerical optimization procedure is affordable on the current generation of supercomputers.
    Keywords: Aircraft Design, Testing and Performance
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  • 69
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    Large Scale Scramjet Propulsion Testing In The Mach 8 and 16 Regime At NASA Ames Research Center (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: The objective of this paper is to describe the affordable, large scale scramJet test capability for flight Mach numbers between 8 and 16 which has been developed at the NASA Ames Research Center. Details of the Direct Connect Arc Facility DCAF, which can produce combustor test conditions with fuel-on testing for 10 seconds at conditions representative of Mach 8 - 12 flight, are presented and typical test results are described. Likewise, a description of the full scale combustor test capability of the 16 inch shock tunnel is outlined. This facility is characterized by long run times (〉 5 milliseconds) for an impulse facility, and it can provide conditions representative of flight conditions from Mach 12 - 16. Typical test results for this shock tunnel are discussed as well. Future upgrades to both facilities are outlined and new uses for their capabilities are discussed.
    Keywords: Aircraft Propulsion and Power
    Type: Twelfth International Symposium on Airbreathing Engines; Sep 10, 1995 - Sep 15, 1995; Melbourne; Australia
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  • 70
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    Reduction of Helicopter BVI Noise, Vibration, and Power Consumption Through Individual Blade Control (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: A wind tunnel test was conducted with a full-scale BO 105 helicopter rotor to evaluate the potential of open-loop individual blade control (IBC) to improve rotor performance, to reduce blade vortex interaction (BVI) noise, and to alleviate helicopter vibrations. The wind tunnel test was an international collaborative effort between NASA/U.S. Army AFDD, ZF Luftfahrttechnik, Eurocopter Deutschland, and the German Aerospace Laboratory (DLR) and was conducted under the auspices of the U.S./German MOU on Rotorcraft Aeromechanics. In this test the normal blade pitch links of the rotor were replaced by servo-actuators so that the pitch of each blade could be controlled independently of the other blades. The specially designed servoactuators and IBC control system were designed and manufactured by ZF Luftfahrttechnik, GmbH. The wind tunnel test was conducted in the 40- by 80-Foot Wind Tunnel at the NASA Ames Research Center. An extensive amount of measurement information was acquired for each IBC data point. These data include rotor performance, static and dynamic hub forces and moments, rotor loads, control loads, inboard and outboard blade pitch motion, and BVI noise data. The data indicated very significant (80 percent) simultaneous reductions in both BVI noise and hub vibrations could be obtained using multi-harmonic input at the critical descent (terminal approach) condition. The data also showed that performance improvements of up to 7 percent could be obtained using 2P input at high-speed forward flight conditions.
    Keywords: Aircraft Design, Testing and Performance
    Type: AHS 51st Annual Forum and Technology Display; May 09, 1995 - May 11, 1995; Fort Worth, TX; United States
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  • 71
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    Propeller/fan-pitch feathering apparatus (1990)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: A pitch feathering system for a gas turbine driven aircraft propeller having multiple variable pitch blades utilizes a counter-weight linked to the blades. The weight is constrained to move, when effecting a pitch change, only in a radial plane and about an axis which rotates about the propeller axis. The system includes a linkage allowing the weight to move through a larger angle than the associated pitch change of the blade.
    Keywords: Aircraft Propulsion and Power
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  • 72
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    Flexible connector for use in aircraft (1992)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The invention concerns a connector, in an aircraft engine, for mounting a ring to a turbine rotor which the ring surrounds. The ring carries propeller blades, and the connector transmits both thrust and torque loads between the ring and the rotor, without significant deformation. However, the connector does deform in order to accommodate differential thermal growth between the ring and the rotor.
    Keywords: Aircraft Design, Testing and Performance
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  • 73
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    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
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  • 74
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    The Design of an Ultra High Capacity Long Range Transport Aircraft (1993)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: This paper examines the design of a 650 passenger aircraft with 8000 nautical mile range to reduce seat mile cost and to reduce airport and airway congestion. This design effort involves the usual issues that require trades between technologies, but must also include consideration of: airport terminal facilities; passenger loading and unloading; and, defeating the 'square-cube' law to design large structures. This paper will review the long range ultra high capacity or megatransport design problem and the variety of solutions developed by senior student design teams at Purdue University.
    Keywords: Aircraft Design, Testing and Performance
    Type: Proceedings of the Ninth Annual Summer Conference: NASA/USRA University Advanced Design Program; 101-111; EP-309
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  • 75
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    Theoretical Investigations on the Efficiency and the Conditions for the Realization of Jet Engines (1950)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Contents: Preliminary notes on the efficiency of propulsion systems; Part I: Propulsion systems with direct axial reaction rockets and rockets with thrust augmentation; Part II: Helicoidal reaction propulsion systems; Appendix I: Steady flow of viscous gases; Appendix II: On the theory of viscous fluids in nozzles; and Appendix III: On the thrusts augmenters, and particularly of gas augmenters
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1259
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  • 76
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    The Design of a Primary Flight Trainer using Concurrent Engineering Concepts (1993)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Concurrent Engineering (CE) concepts seek to coordinate the expertise of various disciplines from initial design configuration selection through product disposal so that cost efficient design solutions may be achieve. Integrating this methodology into an undergraduate design course sequence may provide a needed enhancement to engineering education. The Advanced Design Program (ADP) project at Embry-Riddle Aeronautical University (EMU) is focused on developing recommendations for the general aviation Primary Flight Trainer (PFT) of the twenty first century using methods of CE. This project, over the next two years, will continue synthesizing the collective knowledge of teams composed of engineering students along with students from other degree programs, their faculty, and key industry representatives. During the past year (Phase I). conventional trainer configurations that comply with current regulations and existing technologies have been evaluated. Phase I efforts have resulted in two baseline concepts, a high-wing, conventional design named Triton and a low-wing, mid-engine configuration called Viper. In the second and third years (Phases II and III). applications of advanced propulsion, advanced materials, and unconventional airplane configurations along with military and commercial technologies which are anticipated to be within the economic range of general aviation by the year 2000, will be considered.
    Keywords: Aircraft Design, Testing and Performance
    Type: Proceedings of the Ninth Annual Summer Conference: NASA/USRA University Advanced Design Program; 26-37; EP-309
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  • 77
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    Power turbine ventilation system (1991)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Air control mechanism within a power turbine section of a gas turbine engine. The power turbine section includes a rotor and at least one variable pitch propulsor blade. The propulsor blade is coupled to and extends radially outwardly of the rotor. A first annular fairing is rotatable with the propulsor blade and interposed between the propulsor blade and the rotor. A second fairing is located longitudinally adjacent to the first fairing. The first fairing and the second fairing are differentially rotatable. The air control mechanism includes a platform fixedly coupled to a radially inner end of the propulsor blade. The platform is generally positioned in a first opening and a first fairing. The platform and the first fairing define an outer space. In a first position corresponding with a first propulsor blade pitch, the platform is substantially conformal with the first fairing. In a second position corresponding with the second propulsor blade pitch, an edge portion of the platform is displaced radially outwardly from the first fairing. When the blades are in the second position and rotating about the engine axis, the displacement of the edge portion with respect to the first fairing allows air to flow from the outer space to the annular cavity.
    Keywords: Aircraft Design, Testing and Performance
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  • 78
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    Blade lock for a rotor disk and rotor blade assembly (1992)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A rotor disk 18 and rotor blade 26 assembly is disclosed having a blade lock 66 which retains the rotor blade against axial movement in an axially extending blade retention slot 58. Various construction details are developed which shield the dead rim region D.sub.d and shift at least a portion of the loads associated with the locking device from the dead rim. In one detailed embodiment, a projection 68 from the live rim D.sub.1 of the disk 18 is adapted by slots 86 to receive blade locks 66.
    Keywords: Aircraft Design, Testing and Performance
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  • 79
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    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
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  • 80
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    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
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  • 81
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    Effect of Angle of Incidence of Second-Stage Vane Assembly on Third-Stage Compressor-Blade Vibration and Engine Performance (1951)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Strain-gages were used to measure blade vibrations causing failures in the third stage of a production 11-stage axial-flow compressor. After the serious third-stage vibration was detected, a series of investigations were conducted with second-stage vane assemblies of varying angles of incidence. Curves presented herein show the effect of varying the angle of incidence of second-stage vane assembly on third-stage rotor-blade vibration amplitude and engine performance. A minimum vibration amplitude was obtained without greatly affecting the engine performance with a second-stage vane assembly of 9deg. greater angle of incidence than the assembly normally furnished with the engine.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE51F08
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  • 82
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    Performance of J33-A-27 Turbojet-Engine Compressor (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation was conducted to determine the effects of water injection on the over-all performance of a modified J33-A-27 turbojet-engine compressor at the design equivalent speed of 11,800 rpm. The water-air ratio by weight was 0.05. With water injection the peak pressure ratio increased 9.0 per- cent, the maximum efficiency decreased 15 percent (actual numerical difference 0.12), and. the maximum total weight flow increased 9.3 percent.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE50F14
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  • 83
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    Altitude Performance of J35-A-17 Turbojet Engine in an Altitude Chamber (1951)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation of the altitude performance characteristics of an Allison J35-A-17 turbojet engines have been conducted in an altitude chamber at the NACA Lewis laboratory. Engine performance was obtained over a range of altitudes from 20,000 to 60,000 feet at a flight Mach number of 0.62 and a range of flight Mach numbers from 0.42 to 1.22 at an altitude of 30,000 feet. The performance of the engine over the range investigated could be generalized up to an altitude of 30,000 feet. Performance of the engine at any flight Mach number in the range investigated can be predicted for those operating condition a t which critical flow exits in the exhaust nozzle with the exception of the variables corrected net thrust, and net-thrust specific fuel consumption.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E50I15
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  • 84
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    Investigation of Performance of Axial-Flow Compressor of XT-46 Turbine-Propeller Engine. II - Performance of Revised Compressor at Design Equivalent Speed (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The compressor from the XT-46 turbine-propeller engine was revised by removing the last two rows of stator blades and by eliminating the interstage leakage paths described in a previous report. With the revised compressor, the flow choking point shifted upstream into the last rotor-blade row but the maximum weight flow was not increased over that of the original compressor. The flow range of the revised compressor was reduced to about two-thirds that obtained with the original compressor. The later stages of the compressor did not produce the design static-pressure increase probably because of excessive boundary-layer build-up in this region. Measurements obtained in the ninth-stage stator showed that the performance up to this station was promising but that the last three stages of the compressor were limiting the useful operating range of the preceding stages. Some modifications in flow-passage geometry and blade settings are believed to be necessary, however, before any major improvements in over-all compressor performance can be obtained.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE50J10
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  • 85
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    Summary of Investigations of Mark 25 Aerial-Torpedo Turbine (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The power plant from a Mark 25 aerial torpedo was investigated both as a two-stage turbine and as a single-stage modified turbine to determine the effect on overall performance of nozzle size and shape, first-stage rotor-blade configuration, and axial nozzle-rotor running clearance. Performance was evaluated in terms of brake, rotor, and blade efficiencies. All the performance data were obtained for inlet total to outlet static pressure ratios of 8, 15 (design), and 20 with inlet conditions maintained constant at 95 pounds per square inch gage and 1000 F for rotor speeds from approximately 6000 to 18,000 rpm.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE50D12
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  • 86
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    An Investigation in the Ames 40- by 80-Foot Wind Tunnel of a YT-56A Turboprop Engine Incorporating a Decoupler and a Controlled-Feathering Device (1954)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation of a decoupler and a controlled-feathering device incorporated with the YT-56A turboprop engine has been made to determine the effectiveness of these devices in reducing the high negative thrust (drag) which accompanies power failure of this type of engine. Power failures were simulated by fuel cut-off, both without either device free to operate, and with each device free to operate singly. The investigation was made through an airspeed range from 50 to 230 mph. It was found that with neither device free to operate, the drag levels realized after power failures at airspeeds above 170 mph would impose vertical tail loads higher than those allowable for the YC-130, the airplane for which the test power package was designed. These levels were reached in approximately one second. The maximum drag realized after power failure was not appreciably altered by the use of the decoupler although the decoupler did put a limit on the duration of the peak drag. The controlled-feathering device maintained a level of essentially zero drag after power failure. The use of the decoupler in the YT-56A engine complicates windmilling air-starting procedures and makes it necessary to place operating restrictions on the engine to assure safe flight at low-power conditions,
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SA54I09
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  • 87
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    Multidisciplinary Optimization Methods for Aircraft Preliminary Design (1994)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: This paper describes a research program aimed at improved methods for multidisciplinary design and optimization of large-scale aeronautical systems. The research involves new approaches to system decomposition, interdisciplinary communication, and methods of exploiting coarse-grained parallelism for analysis and optimization. A new architecture, that involves a tight coupling between optimization and analysis, is intended to improve efficiency while simplifying the structure of multidisciplinary, computation-intensive design problems involving many analysis disciplines and perhaps hundreds of design variables. Work in two areas is described here: system decomposition using compatibility constraints to simplify the analysis structure and take advantage of coarse-grained parallelism; and collaborative optimization, a decomposition of the optimization process to permit parallel design and to simplify interdisciplinary communication requirements.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper -94-4325-CP
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  • 88
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    CFD Code Calibration and Inlet-Fairing Effects On a 3D Hypersonic Powered-Simulation Model (1993)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: A three-dimensional (3D) computational study has been performed addressing issues related to the wind tunnel testing of a hypersonic powered-simulation model. The study consisted of three objectives. The first objective was to calibrate a state-of-the-art computational fluid dynamics (CFD) code in its ability to predict hypersonic powered-simulation flows by comparing CFD solutions with experimental surface pressure data. Aftbody lower surface pressures were well predicted, but lower surface wing pressures were less accurately predicted. The second objective was to determine the 3D effects on the aftbody created by fairing over the inlet; this was accomplished by comparing the CFD solutions of two closed-inlet powered configurations with a flowing- inlet powered configuration. Although results at four freestream Mach numbers indicate that the exhaust plume tends to isolate the aftbody surface from most forebody flow- field differences, a smooth inlet fairing provides the least aftbody force and moment variation compared to a flowing inlet. The final objective was to predict and understand the 3D characteristics of exhaust plume development at selected points on a representative flight path. Results showed a dramatic effect of plume expansion onto the wings as the freestream Mach number and corresponding nozzle pressure ratio are increased.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 93-3041
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  • 89
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    An Experimental Parametric Study of Geometric, Reynolds Number, and Ratio of Specific Heats Effects in Three-Dimensional Sidewall Compression Scramjet Inlets at Mach 6 (1993)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: Since mission profiles for airbreathing hypersonic vehicles such as the National Aero-Space Plane include single-stage-to-orbit requirements, real gas effects may become important with respect to engine performance. The effects of the decrease in the ratio of specific heats have been investigated in generic three-dimensional sidewall compression scramjet inlets with leading-edge sweep angles of 30 and 70 degrees. The effects of a decrease in ratio of specific heats were seen by comparing data from two facilities in two test gases: in the Langley Mach 6 CF4 Tunnel in tetrafluoromethane (where gamma=1.22) and in the Langley 15-Inch Mach 6 Air Tunnel in perfect gas air (where gamma=1.4). In addition to the simulated real gas effects, the parametric effects of cowl position, contraction ratio, leading-edge sweep, and Reynolds number were investigated in the 15-Inch Mach 6 Air Tunnel. The models were instrumented with a total of 45 static pressure orifices distributed on the sidewalls and baseplate. Surface streamline patterns were examined via oil flow, and schlieren videos were made of the external flow field. The results of these tests have significant implications to ground based testing of inlets in facilities which do not operate at flight enthalpies.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 93-0740
    Format: application/pdf
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  • 90
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    Information Management for a Large Multidisciplinary Project (1992)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: In 1989, NASA's Langley Research Center (LaRC) initiated the High-Speed Airframe Integration Research (HiSAIR) Program to develop and demonstrate an integrated environment for high-speed aircraft design using advanced multidisciplinary analysis and optimization procedures. The major goals of this program were to evolve the interactions among disciplines and promote sharing of information, to provide a timely exchange of information among aeronautical disciplines, and to increase the awareness of the effects each discipline has upon other disciplines. LaRC historically has emphasized the advancement of analysis techniques. HiSAIR was founded to synthesize these advanced methods into a multidisciplinary design process emphasizing information feedback among disciplines and optimization. Crucial to the development of such an environment are the definition of the required data exchanges and the methodology for both recording the information and providing the exchanges in a timely manner. These requirements demand extensive use of data management techniques, graphic visualization, and interactive computing. HiSAIR represents the first attempt at LaRC to promote interdisciplinary information exchange on a large scale using advanced data management methodologies combined with state-of-the-art, scientific visualization techniques on graphics workstations in a distributed computing environment. The subject of this paper is the development of the data management system for HiSAIR.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 92-4720
    Format: application/pdf
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  • 91
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    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
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  • 92
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    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
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  • 93
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    Preliminary Altitude Operational Characteristics of a J57-P1 Turbojet Engine (1954)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The operational characteristics of a J57-P1 turbojet engine have been investigated at altitudes between 15,000 and 66,000 feet in the Lewis altitude wind tunnel. Included in this study is a discussion of fuel nozzle coking, the altitude operating limits with and without the standard engine control, the compressor surge characteristics, and the engine starting and windmilling characteristics. Severe circumferential turbine outlet temperature gradients which occurred at high altitude as a result of fuel nozzle coking were alleviated by the manufacturer's change in the fuel flow divider schedule and in a nozzle gasket material. Compressor air bleed is required to prevent surge of the outboard compressor in the low engine speed region. The maximum altitude at which the engine was operated without the control was about 66,000 feet at 0.8 flight Mach number and at a reduced engine speed to avoid compressor surge; with the engine control in operation, the altitude operating limit is reduced to approximately 59,000 feet. The maximum altitude at which the engine was started was about 40,000 feet.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE54C31
    Format: application/pdf
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  • 94
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    Effect of Rotor- and Stator-Blade Modifications on Surge Performance of an 11-Stage Axial-Flow Compressor. I - Original Production Compressor of XJ40-WE-6 Engine (1952)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation to increase the compressor surge-limit pressure ratio of the XJ40-WE-6 turbojet engine at high equivalent speeds was conducted at the NACA Lewis altitude wind tunnel. This report evaluates the compressor modifications which were restricted to (1) twisting rotor blades (in place) to change blade section angles and (2) inserting new stator diaphragms with different blade angles. Such configuration changes could be incorporated quickly and easily in existing engines at overhaul depots. It was found that slight improvements in the compressor surge limit were possible by compressor blade adjustment. However, some of the modifications also reduced the engine air flow and hence penalized the thrust. The use of a mixer assembly at the compressor outlet improved the surge limit with no appreciable thrust penalty.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE52G03
    Format: application/pdf
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  • 95
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    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
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  • 96
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    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
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  • 97
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    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
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  • 98
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    High temperature turbine engine structure (1991)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A hybrid ceramic/metallic fastener (bolt) includes a headed ceramic shank carrying a metallic end termination fitting. A conventional cap screw threadably engages the termination fitting to apply tensile force to the fastener.
    Keywords: Aircraft Design, Testing and Performance
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  • 99
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    Aircraft flight path angle display system (1991)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A display system for use in an aircraft control wheel steering system provides the pilot with a single, quickened flight path angle display to overcome poor handling qualities due to intrinsic flight path angle response lags, while avoiding multiple information display symbology. The control law for the flight path angle control system is designed such that the aircraft's actual flight path angle response lags the pilot's commanded flight path angle by a constant time lag .tau., independent of flight conditions. The synthesized display signal is produced as a predetermined function of the aircraft's actual flight path angle, the time lag .tau. and command inputs from the pilot's column.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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  • 100
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    Air turbo-ramjet engine (1991)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A jet engine designed to power a supersonic airplane throughout a range of speeds from subsonic to high supersonic includes a housing which bounds an internal passage having in succession a fixed-area inlet section, a diverging passage section, a mixing section, a combustion section, and an outlet section. A fan rotor rotates in the inlet section and includes a plurality of rotor blade members. The housing includes a main body and at least one flap which is movable between one end position in which it externally bounds a portion of the diverging passage section and another end position in which it externally delimits a diverging discharge passage connecting the diverging passage section with the exterior of the housing. The cross-sectional area of the outlet section is adjustable. The rotor is driven in rotation by a fuel/oxygen powered turbine the outlet of which communicates with the mixing section, but the driving action of the turbine is discontinued at actual supersonic velocities exceeding a predetermined supersonic velocity. The pitch of at least one element of each of the rotor blade members is adjustable.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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