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  • Aircraft Propulsion and Power  (59)
  • Ertrag
  • 1950-1954  (48)
  • 1940-1944  (22)
  • 1935-1939  (14)
  • 1
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    In:  Mitt. Obstbauvers. ring Altes Land, York 7:102-115.
    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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    In:  Prakt. Blätt. Pflanzenb. u. –schutz 14;p. 343-348
    Publication Date: 1937
    Description: Der Autor schildert detailliert den Witterungsverlauf des Vegetationsjahres 1935/36, gibt eine kleine Übersicht über die aufgetretenen Pflanzenkarankheiten und -schädlinge und bringt beides ansatzweise in einen Zusammenhang. Zudem listet er die Erträge des Vegetationsjahres auf und beurteilt diese. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Bayern ; 1936 ; Ertrag ; Getreide ; Niederschlag ; Temperatur ; Wachstum ; Witterung ; Hackfrüchte ; Hochwasser
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  • 3
    Publication Date: 1952
    Description: Untersuchungen über zusammenhänge zwischen Düngung und Ertrag, Witterung und Ertragsbildung, sowie Witterung und Düngewirkung bei den Hauptfrüchten (Winterroggen, Hafer, Kartoffeln) KATASTER-BESCHREIBUNG: Zusammenhang zwischen Witterung (Temperatur und Niederschlag) und der Ertragsbildung sowie zischen der Witterung und der Wirkung der Düngungsarten (mineralisch und organisch) KATASTER-DETAIL: Delta T (März) + und Delta Nied (März) -, dann Trockenschäden an Winterroggen +; kritische Periode (Winterroggen): Wasserversorgung gegen Ende der Blüte; Delta Nied (1. Junihälfte), dann Erträge (Winterroggen) +; Delta T (März) +, dann Schädigung (Hafer) +; Delta T (März) - und Delta Nied (März) +, dann Erträge (Hafer) +; Delta Nied (Ende der Blüte) + und Delta T (Ende August) +, dann Erträge (Kartoffeln) +; Delta Nied (kurz vor dem Ähren- bzw. Rispenschieben) -, dann relative Leistung der organischen Düngung (Winterroggen und Hafer) +; Delta Nied (kurz vor dem Ähren- bzw. Rispenschieben) +, dann Leistung der mineralischen Düngung (Winterroggen und Hafer) +; Delta Nied + (steigend), dann Wirkung mineralischer Düngung +; Delta Nied (Juni) -, dann Wirkung organischer Düngung +,
    Keywords: Thyrow, Brandenburg ; 1936-1952 ; Kartoffeln ; Ertrag ; Hafer ; Roggen ; Witterung ; Düngung
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  • 4
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    In:  Wirtschaft und Statistik , 15, 662, Verlag für Sozialpolitik
    Publication Date: 1935
    Description: Entwicklung der Erträge von Winterroggen, Winterweizen, Sommergerste, Hafer, Kartoffeln, Zuckerrüben, Wiesenheu, Kleeheu in den jeweiligen deutschen Anbaugebieten KATASTER-BESCHREIBUNG: kein Bezug zum Klima KATASTER-DETAIL:
    Keywords: Deutschland ; 1878-1935 ; Zuckerrüben ; Kartoffeln ; Ertrag ; Hafer ; Roggen ; Weizen ; Gerste
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  • 5
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    In:  Forstwiss. Centralbl. Thar. forstl. Jahrb. 66: 115-120
    Publication Date: 1944
    Description: Beschreibung des Ertragsrückgang und der Schäden durch die Spätfröste im Mai 1943 KATASTER-BESCHREIBUNG: Spätfröste verursachten Schäden an Kiefern, Maitriebbildung teilweise extrem gestört und Posthorn- oder kandelaberartige Triebbildung als Folge des Frostes, unterschiedliche Empfindlichkeit der Baumarten KATASTER-DETAIL: Delta T -, (Ende Mai 〈 -6°C), dann schwere Schäden an Walnuss, Eiche, Robinie, Roteiche, Esche, Tanne, mittlere Schiiden:Buche, Roterle, Ahorn, Fichte, Douglasie, Lärche; geringe Schiiden: Roflkastanie,Hainbuche, Linde, Weisserle, Ulme, Birke. Im allgemeinen blieben ohne Schäden: Aspe, Eberesche, Traubenkirsche, Kiefer, Strobe und Bankskiefer.
    Keywords: Nordostdeutschland ; 1943 ; Buche ; Eiche ; Ertrag ; Fichte ; Forst ; Kiefer ; Roterle ; Frost ; Ulme ; Rosskastanie
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  • 6
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    In:  Gartenbauwissenschaft Bd. 17, S.603-615
    Publication Date: 1943
    Description: Einfluss der Temperatur und des Niederschlages auf den Ernteertrag von Birnen und Äpfeln KATASTER-BESCHREIBUNG: Durch Berechnung von Kennziffern zu Wirkung des Sommerregens auf den Obstertrag wird die Bedeutung der Niederschläge in bestimmten Monaten des Vor- und des Erntejahres bestimmt KATASTER-DETAIL: Nied+(Oktober des Vorjahres) und Nied+ (Juli des Erntejahres), dann hohe Erträge von Äpfeln und Birnen
    Keywords: Holstein ; 1916-1935 und 1921-1941 ; Apfel ; Ertrag ; Korrelationsmethode ; Niederschlag ; Rangordnungsmethode ; Temperatur ; Birne
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  • 7
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    In:  Z. f. Acker- und Pflanzenbau 95:233-260
    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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  • 8
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    In:  Die Gartenbauwissenschaft 10: 289-353
    Publication Date: 1937
    Description: Beschreibung der Beziehungen zwischen Ernteerträgen und der Witterung (Temperatur und Niederschlag mithilfe der Rangordungsmethode nach Holdefleiss) in 2 unterschiedlich klimatischen Regionen, Bestimmung von kritischen Zeiten, Auswirkungen auf die Obstsorten und -arten. KATASTER-BESCHREIBUNG: Faktoren Niederschlag und Temperatur haben zu bestimmten Zeiten wichtige Funktionen, schwanken aber zwischen den Arten und Sorten, jedoch Niederschlag ab Mai gewinnt umso mehr an Bedeutung, je geringer die Wasserspeicherkapazität des Bodens, höchster Wasserbedarf im Mai/Juni KATASTER-DETAIL: Delta Temp+ (April im Erntejahr), dann Ertrag ++ Delta Nied Juni (〉63mm Mittel von 1928-33 in Dahlem), dann Ertrag Gravensteiner 〉 115kg Delta Nied+ und Delta Temp+ (Juli-August im Vorjahr), dann Ertrag ++ Delta Nied- (Juli-August im aktuellen Jahr, , dann Ertrag -
    Keywords: Berlin, Hohenheim ; 1909-33, 1907-28 ; Apfel ; Ertrag ; Niederschlag ; Rangordnungsmethode ; Temperatur ; Birne
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  • 9
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    In:  Der Forschungsdienst 2: 581-587
    Publication Date: 1937
    Description: Effekt der Zusatzberegnung auf den Ertrag von Hafer KATASTER-BESCHREIBUNG: Erste Versuche zur Bestimmung des Beregnungszeitpunktes von Getreide KATASTER-DETAIL: Delta Nied+ (Mai 〉 73mm), dann kein Effekt einer zusätzlichen Beregnung auf Ertrag bei Hafer und Gerste (Jahr 1931 und 1932)
    Keywords: Berlin, Brandenburg ; 1934 ; Ertrag ; Hafer ; Niederschlag ; Trockenheit ; Gerste
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  • 10
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    In:  Landwirtschaftl. Jahrbuch 68:642-686
    Publication Date: 1942
    Description: Ableitung kritischer Faktoren (Temperaturoptima und Wasserversorgung) in einzelnen Wachstumsstadien KATASTER-BESCHREIBUNG: Zusammenhang zwischen Temperaturänderung während der Blüte von Weizen und dem Ertrag KATASTER-DETAIL: Delta T + und -: Tmit von 14-15°C, Änderung um +1 K auf 16°C, aber auch Rückgang um 2K auf 13°C, dann Rückgang des Ertrages
    Keywords: Kölner Bucht ; 1907-37 ; Boden ; Ertrag ; Korrelationsmethode ; Niederschlag ; Roggen ; Temperatur ; Weizen ; Witterung ; Düngung ; Hackfrüchte
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  • 11
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    In:  Landwirtschaftl. Jahrbuch 86:823-924.
    Publication Date: 1938
    Description: Erarbeitung einer ausbaufähigen Methode für das Erfassen des Witterungsablaufes; Vergleichen einer Zwölfjahresreihe von Erträgen mit dem Witterungsablauf; bearbeitet wurden Winterroggen, Winterweizen, Wintergerste, Hafer, Sommergerste, Sommerweizen, Kartoffeln KATASTER-BESCHREIBUNG: Zusammenhang Witterung und Ertrag bei Getreide und Kartoffeln KATASTER-DETAIL: Delta Wasserversorgung (Frühjahr) - und Delta Wasserversorgung (Mai, Juni, Juli) +, dann Ertrag (Getreide) +; Delta T (frühe Entwicklungsstadien) -, dann Ertrag (Winterroggen, Hafer) +; Delta T (April) -, dann Ertrag (Hafer) +; Delta Nied (April, Mai) -, dann Ertrag (Winterweizen) +; delta T (Mai) -, dann Ertrag (Winterroggen) +; Delta T +, dann Ertrag (Kartoffel) +; Delta Nied (Juli, August) +, dann Ertrag (Kartoffel) +;
    Keywords: Brandenburg ; 1924-37 ; Kartoffeln ; Ertrag ; Getreide ; Witterung
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  • 12
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    In:  Zeitschr. angew. Meterologie. 56. Jahrgang. Heft 9. S.273-289
    Publication Date: 1939
    Description: Bericht über die Entwicklung von Spätfrösten im norddeutschen Flachland, über die Frühwarnung und über Untersuchungen zur Brauchbarkeit von Frostschutzversuchen KATASTER-BESCHREIBUNG: Einfluss der Temperatur auf den Ertrag KATASTER-DETAIL: Delta T (März) + und Delta T (April) - (Frost), dann Schäden an Obstbäumen + und Ertrag -;
    Keywords: Norddeutschland, Unterelbe ; 1930-1939 ; Boden ; Ertrag ; Temperatur ; Wind ; Witterung ; Globalstrahlung ; Frost ; Obst
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  • 13
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    In:  Kulturtechniker, Berlin 46:19-41.
    Publication Date: 1943
    Description: Bedeutung und Wirkung des Windschutzes auf Anbauart, Fruchtfolge, Gare- und Bodenpflege, Schlageinteilung, Verdunstung, Deck-, Schutz-, Mischfrucht- und Streifenanbau KATASTER-BESCHREIBUNG: Einfluss von Windschutz auf den Ertrag KATASTER-DETAIL: Windschutz +, dann Delta T(Tag) + und Delta T(Nacht)-; Windschutz +, dann Delta Relf +; Windschutz +, dann Verdunstung -; Windschutz +, dann Bodenerosion -; Windschutz +, dann Schneeanhäufung +; angepasste Bodenbearbeitung (schollige, klumpige Bodenoberfläche), dann Wasserhaltungsfähigkeit + -〉 Windschutz +, dann Ertragserhöhung + bzw. ++ (3-400%; ++: Körnerfrüchte auf 20-25vH, Rüben, Gräser, Leguminosen; +: Sommergetreide, Hafer )
    Keywords: weltweit ; letzten100 Jahre ; Boden ; Ertrag ; Niederschlag ; Temperatur ; Verdunstung ; Wind ; Frost
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  • 14
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    In:  Zeitschr. Acker- und Pflanzenbau 98: 145-186
    Publication Date: 1954
    Description: Zusammenwirken von N, P und K bei der Ertragsbildung KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland, Versuchsstationen ; 1900-1953 ; Ertrag ; Witterung ; Düngung
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  • 15
    Publication Date: 1942
    Description: Betrachtung des Klimas (Temperatur und Niederschlag) in Dekaden und Bildung von Ertrags-, Temperatur- und Niederschlagsklassen und daraus Ableitungen über die Beziehungen Ertrag und Witterung KATASTER-BESCHREIBUNG: Einfluss der Witterung (Temperatur, Niederschlag) auf den Ertrag KATASTER-DETAIL: Delta T (März) + und Delta Nied (März) +, dann Erträge +; Delta T (April -, dann Erträge +; Delta Nied (Ende Juni,Ende Juli)-, dann Erträge + Delta T (Anfang Juli) +, dann Erträge +
    Keywords: Schlesien ; 1926-38 ; Boden ; Ertrag ; Niederschlag ; Weizen ; Witterung
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  • 16
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    In:  Landw. Forsch. Darmstadt, 2. Sonderheft: 51-60
    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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  • 17
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    In:  Gesunde Pflanzen 5: 261-263
    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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  • 18
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    In:  Mitteilungen aus der Biologischen Zentralanstalt für Land- und Forstwirtschaft Berlin-Dahlem, Heft 79
    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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  • 19
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    In:  Archiv der wiss. Ges. f. Land- und Forstwirtschaft 2
    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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  • 20
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    In:  Diss. Halle (Saale), Kühn-Archiv, Band 42, 1936
    Publication Date: 1936
    Description: Rangordnungsmethode nach Holdefleiß zur qualitativen Ertragsanalyse, Untersucht wurden die Erträge von Roggen, Weizen, Gerste, Hafer, Erbsen, Pferdebohnen, Hackfrüchte, Rübensamen, Zuckerrüben, Futterrüben, Kartoffeln KATASTER-BESCHREIBUNG: Einfluss der Witterung auf den Ertrag KATASTER-DETAIL: Delta Sonn (Winter) +, dann Ertrag (Roggen und Weizen) +; Delta T (Winter, September bis März) + und Delta T (Mai, Juni) -, dann Ertrag (Gerste) +; Delta Sonn (Winter) +, dann Ertrag (Sommergetreide) +; Delta T (April, Mai) - und Delta Nied (April, Mai) +, dann Ertrag (Weizen) +; Delta T (Mai bis Juli) - und Delta Nied (Mai bis Juli) +, dann Ertrag (Gerste) +; Delta Nied (April bis Juni) -, dann Ertrag (Hafer) -; Delta Sonn (März) +, dann Ertrag (Hafer) +; Delta Sonn (März) + und Delta T (Mai bis Erntezeit) -, dann Ertrag (Viktoria-Erbse) +; Delta Sonn (Winter) + und Delta Nied (Sommer) +, dann Ertrag (Pferdebohnen) +; Delta Nied +, dann Ertrag (Hackfrüchte) +; Delta Sonn (März, April) +, dann Ertrag (Zuckerrüben) +; Delta Sonn (Winter) +, dann Ertrag (Futterrüben) +; Delta T (September, Oktober - Vorjahr) + und Delta Nied (September, Oktober - Vorjahr) -, dann Ertrag (Kartoffeln) +; Delta Sonn (Winter) +, dann Ertrag (Kartoffeln) +; Delta Nied (April bis Agust) +, dann Ertrag (Kartoffeln) +;
    Keywords: Eichsfeld und Thüringer Becken ; 1900-1931 ; Ertrag ; Getreide ; Niederschlag ; Rangordnungsmethode ; Temperatur ; Trockenheit ; Wassermangel ; Witterung
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  • 21
    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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  • 22
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    In:  Mitteilungen für die Landwirtschaft 51(Heft 46).
    Publication Date: 1936
    Description: Beobachtungen zum Ernteausfall und dessen Beeinflussung durch den Witterungsverlauf im Jahr 1936. Vergleich mit vergangenen Jahren. KATASTER-BESCHREIBUNG: Zusammenhang zwischen Temperatur und Niederschlag in den Monaten April, Mai und Juni und den Reichsertragsschätzungen, bzw. den tatsächlichen Erträgen. Bedeutung eines längeren warmen und niederschlagsarmen Junis für Getreide. KATASTER-DETAIL: Delta T (Juni) -, dann Erträge + Delta T (Juni) + und Niederschlage -, dann Ersträge -
    Keywords: Deutschland ; 1930-1936 ; Ertrag ; Getreide ; Landwirtschaft ; Niederschlag ; Temperatur ; Trockenheit
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  • 23
    Publication Date: 1937
    Description: Untersuchungen zur Bedeutung der Winterfeuchtigkeit für Roggen bis etwa zum Zeitpunkt des Ährenschiebens, Wechselwirkung Sonnenscheindauer, Temperatur und Niederschlag in unterschiedlichen phänologischen Stadien bei unterschiedlichen Roggensorten und variierender Stickstoffgabe KATASTER-BESCHREIBUNG: Einfluss der Witterung (Sonnenschein, Temperatur, Niederschlag)auf das Wachstum KATASTER-DETAIL: Delta Sonn -, dann Längenwachstum +; Winterfeuchtigkeit +, dann Wachstum +; Delta Nied (von N-Düngung bis Ährenschieben) - und Delta T (von N-Düngung bis Ährenschieben) +, dann Längenwachstum = max; Delta Nied (Hauptvegetationszeit) +, Delta T (Hauptvegetationszeit) -, Delta Sonn (Hauptvegetationszeit) -, dann Längenwachstum +; Delta Nied (Hauptvegetationszeit) + und Delta Wind (Hauptvegetationszeit) +, dann Lagerbildung +;
    Keywords: Brandenburg, Versuchsfeld Bornim bei Potsdam ; 1932-36 ; Ertrag ; Landwirtschaft ; Niederschlag ; Roggen ; Temperatur ; Wachstum ; Düngung
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  • 24
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    In:  Klima / Boden / Ernte Verlag C.V. Engelhard, Berlin. p. 7, 114-127
    Publication Date: 1942
    Description: Beziehung zwischen Witterungsablauf und Bodenzustand und deren Auswirkung auf Pflanzenwuchs und Ernte KATASTER-BESCHREIBUNG: Einfluss der Witterung auf den Ertrag von Kartoffeln KATASTER-DETAIL: Delta T (April bis Juli) -, dann Erträge (Kartoffel) +; Delta Nied (April bis Juli) -, dann Erträge (Kartoffel) -
    Keywords: Gesamtpreußen, Deutschland,Schlesien ; 1921-1932,1934 ; Zuckerrüben ; Kartoffeln ; Ertrag ; Hafer ; Landwirtschaft ; Niederschlag ; Temperatur ; Witterung ; Hackfrüchte
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  • 25
    Publication Date: 1950
    Description: Einfuß der Temperatur, Sonnenscheindauer und des Niederschages auf die Reifedauer des Roggens KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland ; 1936-37 ; Ertrag ; Phänologie ; Roggen ; Trockenheit ; Wachstum ; Witterung
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  • 26
    Publication Date: 2018-08-03
    Description: The development of new cowlings, applicable to a short-nose radial engine, is described. These cowlings, designated the NACA cowlings D(sub s) and D(sub sf), employ a larger spinner and a higher inlet-velocity ratio than does the conventional NACA cowling C. The pressures available for cooling and the estimated critical Mach number were found to be higher with the new cowlings than are usually encountered with the conventional NACA cowling C. Large-chord propeller cuffs were found to have a stabilizing effect on the flow entering the cowling and resulted in increased front pressures. Fan blades mounted on the spinner in the inlet opening had a similar effect.
    Keywords: Aircraft Propulsion and Power
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  • 27
    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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  • 28
    Publication Date: 2019-06-28
    Description: Following a brief history of the NACA investigation of jet-propulsion, a discussion is given of the general investigation and analyses leading to the construction of the jet-propulsion ground-test mock-up. The results of burning experiments and of test measurements designed to allow quantitative flight-performance predictions of the system are presented and correlated with calculations. These calculations are then used to determine the performance of the system on the ground and in the air at various speeds and altitudes under various burning conditions. The application of the system to an experimental airplane is described and some performance predictions for this airplane are made. It was found that the main fire could be restricted to an intense, small, and short annular blue flame burning steadily and under control in the intended combustion space. With these readily obtainable combustion conditions, the combustion chamber the nozzle walls and the surrounding structure could be maintained at normal temperatures. The system investigated was found to be capable of burning one-half the intake air up the fuel rates of 3 pounds per second. Calculations were shown to agree well with experiment. It was concluded that the basic features of the jet-propulsion system investigation in the ground-test mock-up were sufficiently developed to be considered applicable to flight installation. Calculations indicated that an airplane utilizing this jet-propulsion system would have unusual capabilities in the high-speed range above the speeds of conventional aircraft and would, in addition, have moderately long cruising ranges if only the engine were used.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-L-528 , NACA-ACR-L4D26
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  • 29
    Publication Date: 2019-06-28
    Description: Engine tests, together with estimates made at Langley Memorial Aeronautical Laboratory, indicate that a 25-percent increase in take-off power can be obtained with present-day aircraft engines without increasing either the knock limit of the fuel or the external cooling requirements of the engine. This increase in power with present fuels and present external cooling is made possible through the use of an internal coolant inducted through the inlet manifold. Estimates on aircraft indicate that this 25-percent increase in power will permit an approximate usable increase of 8.5 percent in the take-off load of existing military airplanes. This increase in load is equivalent to an increase in the weight of gasoline normally carried of between 30 and 65 percent.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-E-117 , NACA-RB-4A25
    Format: application/pdf
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  • 30
    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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  • 31
    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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  • 32
    Publication Date: 2019-06-28
    Description: Tests of four 10-foot propellers were made in the propeller-research tunnel for the Army Air Corps to check flight and static thrust test results made on several propellers embodying Clark Y and modified NACA 16-series sections. These propellers were identical as to diameter and activity factor and very closely identical in thickness ratio and pitch distribution. The blades embodied sections with both single- and double-cambered Clark Y, modified NACA 16-series, and a combination of Clark Y and modified NACA-16 airfoils. Tests covered a range of blade angles from 20 deg. to 70 deg., and were all made at tip speeds below 280 feet per second. Although these tests were not conclusive in themselves, owing to the conditions under which they were made, the results seem to check the flight and static tests as closely as would be expected.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-L-569
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  • 33
    Publication Date: 2019-06-28
    Description: A thermocouple was installed in the crown of a sodium-cooled exhaust valve. The valve was then tested in an air-cooled engine cylinder and valve temperatures under various engine operating conditions were determined. A temperature of 1337 F was observed at a fuel-air ratio of 0.064, a brake mean effective pressure of 179 pounds per square inch, and an engine speed of 2000 rpm. Fuel-air ratio was found to have a large influence on valve temperature, but cooling-air pressure and variation in spark advance had little effect. An increase in engine power by change of speed or mean effective pressure increased the valve temperature. It was found that the temperature of the rear spark-plug bushing was not a satisfactory indication of the temperature of the exhaust valve.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-E-140 , NACA-ARR-3L06
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  • 34
    Publication Date: 2019-06-28
    Description: An investigation was made to determine a method of measuring fuel-air ratio that could be used for test purposes in flight and for checking conventional equipment in the laboratory. Two single-cylinder test engines equipped with typical commercial engine cylinders were used. The fuel-air ratio of the mixture delivered to the engines was determined by direct measurement of the quantity of air and of fuel supplied and also by analysis of the oxidized exhaust gas and of the normal exhaust gas. Five fuels were used: gasoline that complied with Army-Navy fuel Specification No. AN-VV-F-781 and four mixtures of this gasoline with toluene, benzene, and xylene. The method of determining the fuel-air ratio described in this report involves the measurement of the carbon-dioxide content of the oxidized exhaust gas and the use of graphs for the presented equation. This method is considered useful in aircraft, in the field, or in the laboratory for a range of fuel-air ratios from 0.047 to 0.124.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TR-757
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  • 35
    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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  • 36
    facet.materialart.
    Unknown
    In:  CASI
    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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  • 37
    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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  • 38
    Publication Date: 2019-07-13
    Description: Hot-air engines with dynamic compressors and turbines offer new prospects of success through utilization of units of high efficiencies and through the employment of modern materials of great strength at high temperature. Particular consideration is given to an aerodynamic prime mover operating on a closed circuit and heated externally. Increase of the pressure level of the circulating air permits a great increase of limit load of the unit. This also affords a possibility of regulation for which the internal efficiency of the unit changes but slightly. The effect of pressure and temperature losses is investigated. A general discussion is given of the experimental installation operating at the Escher Wyss plant in Zurich for a considerable time at high temperatures.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1034 , Zeitschrift des Vereines Deutscher Lagenieure; 85; 22; 491-500
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  • 39
    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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  • 40
    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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  • 41
    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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  • 42
    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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  • 43
    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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  • 44
    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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  • 45
    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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  • 46
    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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  • 47
    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
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  • 48
    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
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  • 49
    facet.materialart.
    Unknown
    In:  CASI
    Publication Date: 2019-08-13
    Description: The performance of a jet power plant consisting of a compressor and a turbine is determined by the characteristic curves of these component parts and is controllable by the characteristics of the compressor and the turbine i n relation t o each other. The normal. output, overload, and throttled load of the Jet power plant are obtained on the basis of assumed straight-line characteristics.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1258
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  • 50
    Publication Date: 2019-08-13
    Description: Following a brief history of the NACA investigation of jet propulsion, a discussion is given of the general investigation and analysis leading to the construction of the jet-propulsion ground-test mock-up. The results of burning experiments and of test measurements designed to allow quantitative flight performance predictions of the system are presented and correlated with calculations. These calculations are then used to determine the performance of the system on the ground and in the air at various speeds and altitudes under various burning conditions. The application of the system to an experimental airplane is described and some performance predictions for this airplane are made.
    Keywords: Aircraft Propulsion and Power
    Type: NACA/TR-802
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  • 51
    Publication Date: 2019-07-11
    Description: This paper presents the results of tests conducted to determine the effect of the constructional elements of a Laval nozzle on the velocity and pressure distribution and the magnitude of the reaction force of the jet. The effect was studied of the shapes of the entrance section of the nozzle and three types of divergent sections: namely, straight cone, conoidal with cylindrical and piece and diffuser obtained computationally by a graphical method due to Professor F. I. Frankle. The effect of the divergence angle of the nozzle on the jet reaction was also investigated. The results of the investigation showed that the shape of the generator of the inner surface of the entrance part of the nozzle essentially has no effect on the character of the flow and on the reaction. The nozzle that was obtained by graphical computation assured the possibility of obtaining a flow for which the velocity of all the gas particles is parallel to the axis of symmetry of the nozzle, the reaction being on the average 2 to 3 percent greater than for the usual conical nozzle under the same conditions, For the conical nozzle the maximum reaction was obtained for a cone angle of 25deg to 27deg. At the end of this paper a sample computation is given by the graphical method. The tests were started at the beginning of 1936 and this paper was written at the same time.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1066 , Report of the Central Aero-Hydrodynamical Inst., Moscow; Rept-478
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  • 52
    Publication Date: 2019-07-11
    Description: An investigation was conducted at simulated high-altitude flight conditions to evaluate the use of compressor evaporative cooling as a means of turbojet-engine thrust augmentation. Comparison of the performance of the engine with water-alcohol injection at the compressor inlet, at the sixth stage of the compressor, and at the sixth and ninth stages was made. From consideration of the thrust increases achieved, the interstage injection of the coolant was considered more desirable preferred over the combined sixth- and ninth-stage injection because of its relative simplicity. A maximum augmented net-thrust ratio of 1.106 and a maximum augmented jet-thrust ratio of 1.062 were obtained at an augmented liquid ratio of 2.98 and an engine-inlet temperature of 80 F. At lower inlet temperatures (-40 to 40 F), the maximum augmented net-thrust ratios ranged from 1.040 to 1.076 and the maximum augmented jet-thrust ratios ranged from 1.027 to 1.048, depending upon the inlet temperature. The relatively small increase in performance at the lower inlet-air temperatures can be partially attributed to the inadequate evaporation of the water-alcohol mixture, but the more significant limitation was believed to be caused by the negative influence of the liquid coolant on engine- component performance. In general, it is concluded that the effectiveness of the injection of a coolant into the compressor as a means of thrust augmentation is considerably influenced by the design characteristics of the components of the engine being used.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E52F20
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  • 53
    Publication Date: 2019-07-11
    Description: This report presents a compilation of static sea-level data on existing or designed American and British axial-flow turbojet engines in terms of basic engine parameters such as thrust and air flow. In the data presented, changes in the over-U engine performance with time sre examined as well as the relation of the various engine parameters to each other.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-51K29
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  • 54
    Publication Date: 2019-07-10
    Description: An investigation was made of the performance of nine conical cooling-air ejectors at primary jet pressure ratios from 1 to 10, secondary pressure ratios to 4.0, and a temperature ratio of unity. This phase of the investigation was limited to conical ejectors having shroud exit to primary nozzle exit diameter ratios of 1.06 and 1.40, with several spacing ratios for each. The experimental results indicated that the pumping range and amount of cooling-air flow obtained with a 1.06 diameter ratio ejector were relatively small for cooling purposes but that the maximum possible thrust loss, which occurred with no secondary flow, was only 7 percent of convergent nozzle thrust. The 1.40 diameter ratio ejector produced a large cooling air flow and showed a possible thrust loss of 29.5 percent with no cooling air flow. Thrust gains were attained with ejectors of both diameter ratios at secondary pressure ratios greater than 1.0. The limiting primary pressure ratio below which an ejector can operate at a specific secondary pressure ratio (cut-off point) may be estimated for various flight conditions from data contained herein.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E52F26
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  • 55
    Publication Date: 2019-09-20
    Description: The performance of a two-stage turbine with variable-area first-stage turbine nozzles was determined in the NACA Lewis altitude wind tunnel over a range of simulated altitudes from 15,000 to 44,000 feet and engine speeds from 50 to 100 percent of rated speed. The variable-area turbine nozzles used in this investigation were primarily a test device for compressor research purposes and were not necessarily of optimum aerodynamic design. The results of this investigation are indicative of effects of turbine-nozzle-area variation on turbine performance within the operating range allowed by the engine. The variable-area turbine nozzles were found to be mechanically reliable and to have negligible leakage losses. Increasing the turbine-nozzle-throat area from 1.15 to 1.67 square feet increased the corrected turbine gas flow or effective turbine nozzle area about 10 percent. At a given corrected turbine speed and turbine pressure ratio, changing the turbine nozzle area from 1.30 to 1. 67 square feet lowered the turbine efficiency 3 or 4 percent. The effect of increasing the turbine nozzle area from 1.15 to 1.67 square feet (decreasing the turning angle about 7 1/2 degrees) would be to lower the turbine efficiency about 5 or 6 percent.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E52J20
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  • 56
    facet.materialart.
    Unknown
    In:  CASI
    Publication Date: 2019-07-13
    Description: The following investigations are connected with experiments on fans carried out by the author in the Gouttingen Aerodynamic Laboratory within the framework of the preliminary experiments for the new Gouttingen wind-tunnel project. A fan rotor was developed which had very high efficiency at the design point corresponding to moderate pressure and which, in addition, could operate at a proportionally high pressure, rise. To establish the determining operating factors the author carried out extensive theoretical investigation in Hannover. In this it was necessary, to depart from the usual assumption of vanishing radial velocities. The calculations were substantially lightened by the introduction of diagrams. The, first part of the.report describes the theoretical investigations; the second, the experiments carried out at Gouttingen.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1062 , Luftfahyrtforschung; 14; 7; 325-346
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  • 57
    Publication Date: 2019-07-11
    Description: To determine the effect of piston-head temperature on knock-limited power. Tests were made in a supercharged CFR engine over a range of fuel-air ratios from 0.055 to 0.120, using S-3 reference fuel, AN-F-28, Amendment-2, aviation gasoline, and AN-F-28 plus 2 percent xylidines by weight. Tests were run at a compression ratio of 7.0 with inlet-air temperatures of 150 F and 250 F and at a compression ratio of 8.0 with an inlet-air temperature of 250 F. All other engine conditions were held constant. The piston-head temperature was varied by circulation of oil through passages in the crown of a liquid-cooled piston. This method of piston cooling decreased the piston-head temperature about 80 F. The data are not intended to constitute a recommendation as to the advisability of piston cooling in practice.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-E-35 , NACA-ARR-E4G13
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  • 58
    Publication Date: 2019-07-11
    Description: Performance data obtained with recording oscillographs are presented to show the transient response of the General Electric Integrated Electronic Control operating on the J47 RXl-3 turbo-Jet engine over a range of altitudes from 10,000 to 45,000 feet and at ram pressure ratios of 1.03 and 1.4. These data represent the performance of the final control configuration developed after an investigation of the engine transient behavior in the NACA altitude wind tunnel. Oscillograph traces of controlled accelerations (throttle bursts),oontrolled decelerations (throttle chops), and controlled altitude starts are presented.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE50G12
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  • 59
    Publication Date: 2019-07-11
    Description: A method has been developed for modifying a rocket motor so that its exhaust characteristics simulate those of a turbojet engine. The analysis necessary to the design is presented along with tests from which the designs are evaluated. Simulation was found to be best if the exhaust characteristics to be duplicated were those of a turbojet engine at high altitudes and with the afterburner operative.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-L54I15
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  • 60
    Publication Date: 2019-07-11
    Description: A modified J33-A-27 compressor was operated over a range of equivalent impeller speeds from 6100 to 13,250 rpm in order to obtain the over-all compressor performance. At the equivalent design speed of 11,800 rpm, the maximum efficiency of 0.764 and peak pressure ratio of 4.56 occurred at an equivalent weight flow of 104.07 pounds per second. At the highest equivalent speed (13,250 rpm) a maximum efficiency of 0.711, a maximum equivalent weight flow of 123.00 pounds per second, and a peak pressure ratio of 5.76 were obtained.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE50D25
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  • 61
    Publication Date: 2019-07-12
    Description: Component data on the J35-A-23 compressor and two-stage turbine were used to determine the problems in matching the two units for operatio n in a turbojet engine. Possible operating regions were determined an d an equilibrium operating line was also determined for the assumed c onditions of zero flight speed and a jet nozzle area approximately 5. 5 percent greater than the wide-open nozzle area.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E51H15
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  • 62
    Publication Date: 2019-07-12
    Description: The stator-blade angles in the twelfth to fifteenth stages of a 16-stage high-pressure-ratio axial-flow compressor were decreased 3 deg The over-all performance of this compressor is compared with the performance of the same compressor with standard blade angles. The matching characteristics of the modified compressor and a two-stage turbine were also obtained and compared with those of the compressor with the original blade angles and the same turbine.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E51L03
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  • 63
    Publication Date: 2019-07-12
    Description: The performance of a 13-stage development comressor for the J40-WE-24 engine has been determined at equivalent speeds from 30 to 112 percent of design. The design total-pressure ratio of 6.0 and the design weight flow of 164 pounds per second were not attained, An analysis was conducted to determine the reasons for the poor performance at the design and over-design speed. The analysis indicated that most of the difficulty could be attributed to the fact that the first stage was overcompromised to favor part-speed performance,
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE53D17
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  • 64
    Publication Date: 2019-07-12
    Description: A .General Electric fuel and torque regulator was tested in conjunction with a T31-3 turbine-propeller engine in the sea-level static test stand at the NACA Lewis laboratory. The engine and control were operated over the entire speed range: 11,000 rpm, nominal flight idle, to 13,000 rpm, full power. Steady-state and transient data were recorded and are presented with a description of the four control loops being used in the system. Results of this investigation indicated that single-lever control operation was satisfactory under conditions of test. Transient data presented showed that turbine-outlet temperature did overshoot maximum operating value on acceleration but that the time duration of overshoot did not exceed approximately 1 second. This temperature limiting resulted from a control on fuel flow as a function of engine speed. Speed and torque first reached their desired values 0.4 second from the time of change in power-setting lever position. Maximum speed overshoot was 3 percent.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE1H20
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  • 65
    Publication Date: 2019-07-12
    Description: Altitude performance of a YJ71-A-7 turbojet engine, with afterburner inoperative, was determined in the NACA Lewis altitude wind tunnel over a wide range of flight conditions. Engine speed and exhaust-nozzle area were controlled independently during this investigation. The variation of corrected values of air flow, net thrust, and fuel flow with corrected engine speed was not defined by a single curve with changes in altitude at given flight Mach number. Changes in altitude had very little effect on minimum specific fuel consumption at altitudes up to 45,000 feet. There is one exhaust-nozzle schedule that is nearly optimum for all flight conditions. Performance calculated from pumping characteristics agreed with experimental values and can therefore be used to extend engine performance data.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E53E13
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  • 66
    Publication Date: 2019-07-12
    Description: At the request of the Bureau of Aeronautics, Department of the Navy, an investigation of the Westinghouse XJ34-WE-32 turbojet engine is being conducted in the NACA Lewis altitude wind tunnel to determine the steady-state and transient operating characteristics of the controlled and uncontrolled engine at various altitudes and ram pressure ratios. As part of this program, transient performance data that illustrate the operation of the engine is obtained in the form of oscillographic traces. Similar data for engine operation i n the afterburning range, covering a range of throttle settings from the minimum value giving rated speed (throttle position, 72 degrees) to full afterburning (throttle position, ll0 degrees), is presented herein. These data thus serve to indicate the transient characteristics of the engine when the throttle is advance into, withdrawn from, and moved within the afterburning range in a stepwise manner, as well as the steady-state stability of the engine during afterburning .
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE50L29
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  • 67
    Publication Date: 2019-07-12
    Description: The Pratt and Whitney Aircraft company and the Naval Aircraft Factory of the United States Navy cooperated in a laboratory and flight program of tests on an exhaust turbine supercharger. Two series of dynamometer tests of the engine super-charger combination were completed under simulated altitude conditions. One series of hot gas-chamber tests was conducted by the manufacturer of the supercharger. Flight demonstrations of the supercharger installed in a twin-engine flying boat were terminated by failure of the turbine wheels. The analysis of the results indicated that a two-stage supercharger with the first-stage exhaust turbine driven will deliver rated power for a given indicated power to a higher altitude, will operate more efficiently, and will require simpler controls than a similar engine with the first stage of the supercharger driven from the crankshaft through multispeed gears.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-194
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  • 68
    Publication Date: 2019-07-12
    Description: Tests were made in the 20-foot propeller-research tunnel to investigate the possibility of obtaining increased net efficiencies of propeller-nacelle units by enclosing the engines in the wings and by using extension shafts. A wing of 5-foot chord was fitted with a propeller drive assembly providing for several axial locations of tractor propellers and pusher propellers. A three-blade 4-foot propeller and a three-blade 3 1/2-foot propeller of special design were tested in this wing with spinners and fairings ranging in diameter from 6 to 16 inches. A 16-inch NACA cowling was tested for comparative purposes. Two types of cuffs were also employed. It was found that the net efficiency of a conventional round-shank propeller mounted on an extension shaft in front of or behind a wing increased with an increase in the diameter of the spinner and the shaft housing within the scope of the tests. The largest spinner used had a diameter that might favorably compare with that of a radial engine cowling. The efficiencies for the pusher position appeared to be more critically affected by spinner size than those for the tractor position. The spinners with large diameters for the pusher position resulted in a higher efficiency than those for the corresponding tractor arrangements; the reverse was true for the small spinners. The use of propeller cuffs in combination with a spinner of small diameter generally resulted in net efficiencies that were comparable with those found for the large-spinner combinations.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-196
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  • 69
    Publication Date: 2019-07-12
    Description: A theoretical method for evaluating the stability characteristics and the amplitude and the frequency of pulsation of ram-jet engines without heat addition is presented herein. Experimental verification of the theoretical results are included where data were available. Theory and experiment show that the pulsation amplitude of a high mass-flow-ratio diffuser having no cone surface flow separation increases with decreasing mass flow. The theoretical trends for changes in amplitude, frequency, and mean-pressure recovery with changes in plenum-chamber volume were experimentally confirmed. For perforated convergent-divergent-type diffusers, a stability hysteresis loop was predicted on the pressure-recovery mass-flow-ratio curve. At a given mean mass-flow ratio, the higher.value of mean pressure recovery corresponded to oscillatory flow in the diffuser while the lower branch was stable. This hysteresis has been observed experimentally. The theory indicates that for a ram-jet engine of given diameter, the amplitude of pulsation of a supersonic diffuser is increased by decreasing the relative size of the plenum chamber with respect to the diffuser volume down to a critical value at which oscillations cease. In the region of these critical values, the stable mass-flow range of the diffuser may be increased either by decreasing the combustion chamber volume or by increasing the length of the diffuser.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E52I24
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  • 70
    facet.materialart.
    Unknown
    In:  CASI
    Publication Date: 2019-07-12
    Description: Tests of three-blade, adjustable-pitch counterrotating tandem model propellers, adjusted to absorb equal power at maximum efficiency of the combination, were made at Stanford University. The aerodynamic characteristics, for blade-angle settings of 15, 25, 35, 45, 55, and 65 degrees at 0.75R of the forward propeller and for diameters spacings of 8-1/2, 15 and 30% were compared with those of three-blade and six-blade propellers of the same blade form. It was found that, in order to realize the condition of equal power at maximum efficiency, the blade angles for the rear propeller must be generally less than for the forward propeller, the difference increasing the blade angle. The tests showed that, at maximum efficiency, the tandem propellers absorb about double the power of three-blade propellers and about 8% more power than six-blade propellers having the pitch of the forward propeller of the tandem combination. The maximum efficiency of the tandem propellers was found to be from 2-15% greater than for six-blade propellers, the difference varying directly with blade angle. It was also found that the maximum efficiency of the tandem propellers was greater than that of a three-blade propeller for blade angles at 0.75R of 25 degrees or more. The difference in maximum efficiency again varied directly with blade angle, being about 9% for 65 degrees at 0.75R.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-126
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  • 71
    Publication Date: 2019-07-12
    Description: Engine and airplane performance data have been gathered from various sources and analyzed to determine indications of the most economical methods of flight operation from a consideration of fuel expenditure. The analysis includes the influence of such facts as fuel-air ratio, engine speed, engine knock, altitude, cylinder cooling, spark timing, and limits of cruising brake mean effective pressure. The results indicate that the cheapest power is obtained with approximately correct mixture at low engine speed and highest permissible manifold pressure. If more power is desired, the methods of obtaining it are, in order of fuel economy: (a) increasing the engine speed and maintaining safe cylinder temperatures by cooling; (b) retarding the spark or cooling further to permit higher manifold pressure; and, (c) riching the mixture. The analysis further shows that the maximum time endurance of flight occurs at the air speed corresponding to minimum thrust horsepower required and with minimum practicable engine speed. Maximum mileage per pound of fuel is obtained at slightly higher air speed. The fuel-air ratio should be approximately the theoretically correct ratio in both cases. For an engine equipped with a geared supercharger, as in the example presented, and with knock as the limiting condition, a comparison of operation at sea level and at 6,000 feet shoes flight at altitude to be more economical on the basis of both range and endurance.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-134
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  • 72
    Publication Date: 2019-07-12
    Description: This investigation presents the results of tests made on a radial engine to determine the thrust that can be obtained from the exhaust gas when discharged from separate stacks and when discharged from the collector ring with various discharge nozzles. The engine was provided with a propeller to absorb the power and was mounted on a test stand equipped with scales for measuring the thrust and engine torque. The results indicate that at full open throttle at sea level, for the engine tested, a gain in thrust horsepower of 18 percent using separate stacks, and 9.5 percent using a collector ring and discharge nozzle, can be expected at an air speed of 550 miles per hour.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-139
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  • 73
    Publication Date: 2019-07-12
    Description: An investigation is in progress in the NACA full-scale wind tunnel to determine the drag and propulsive efficiency of nacelle sizes. In contrast with the usual tests with a single nacelle, these tests were conducted with nacelle-propeller installations on a large model of a 4-engine airplane. Data are presented on the first part of the investigation, covering seven nacelle arrangements with nacelle diameters from 0.53 to 1.5 times the wing thickness. These ratios are similar to those occurring on airplane weighing from about 20 to 100 tons. The results show that the drag, the propulsive efficiency, and the overall efficiency of the various nacelle arrangements as functions of the nacelle size, the propeller position, and the airplane lift coefficient. The effect of the nacelles on the aerodynamic characteristics of the model are shown for both propeller-removed and propeller-operating conditions.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-122
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  • 74
    Publication Date: 2019-07-12
    Description: In the design of a cowling a certain pressure drop across the cylinders of a radial air-cooled engine is made available. Baffles are designed to make use of this available pressure drop for cooling. The problem of cooling an air-cooled engine cylinder has been treated, for the most part, from considerations of a large heat-transfer coefficient. The knowledge of the precise cylinder characteristics that give a maximum heat-transfer coefficient should be the first consideration. The next problem is to distribute this ability to cool so that the cylinder cools uniformly. This report takes up the problem of the design of a baffle for a model cylinder. A study has been made of the important principles involved in the operation of a baffle for an engine cylinder and shows that the cooling can be improved 20% by using a correctly designed baffle. Such a gain is as effective in cooling the cylinder with the improved baffle as a 65% increase in pressure drop across the standard baffle and fin tips.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-64
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  • 75
    Publication Date: 2019-07-12
    Description: Flight test s were conducted on the XP-41 airplane, equipped with a Pratt & Whitney R1830-19, 14-cylinder, air-cooled engine, to determine the increase in flight speed obtainable by the use of individual exhaust stacks directed rearwardly to obtain exhaust-gas thrust. Speed increases up to 18 miles per hour at 20,000 feet altitude were obtained using stacks having an exit area of 3.42 square inches for each cylinder. A slight increase in engine power and decrease in cylinder temperature at a given manifold pressure were obtained with the individual stacks as compared with a collector-ring installation. Exhaust-flame visibility was quite low, particularly in the rich range of fuel-air ratios.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-165
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  • 76
    Publication Date: 2019-07-12
    Description: A program was undertaken to determine the J73 turbojet engine compressor stall and surge characteristics and combustor blow-out limits encountered during transient engine operation. Data were obtained in the form of oscillograph traces showing the time history of several engine performance parameters with changes in engine fuel flow. The data presented in this report are for step changes in fuel flow at an altitude of 35,000 feet, at flight Mach numbers of 0.3, 0.8, and 1.2, and at several engine-inlet temperatures,
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE53F29
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  • 77
    Publication Date: 2019-07-12
    Description: This report summarizes the effects of fuel volatility and engine design variables on the problem of starting gas-turbine engines at sea-level and altitude conditions. The starting operation for engines with tubular combustors is considered as three steps; namely, (1) ignition of a fuel-air mixture in the combustor, (2) propagation of flame through cross-fire tubes to all combustors, and (3) acceleration of the engine from windmilling or starting speed to the operating speed range. Pertinent data from laboratory researches, single-combustor studies, and full-scale engine investigations are presented on each phase of the starting problem.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE51B02
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  • 78
    facet.materialart.
    Unknown
    In:  CASI
    Publication Date: 2019-08-26
    Description: Tests of 2-blade, adjustable-pitch, counterrotating tandem model propellers, adjusted to absorb equal power at maximum efficiency, were made at Stanford University. The characteristics, for 15 degrees, 25 degrees, 35 degrees, and 45 degrees pitch settings at 0.75 R of the forward propeller and for 8 1/2%, 15% and 30% diameter spacings, were compared with those of 2-blade and 4-blade propellers of the same blade form. The tests showed that the efficiency of the tandem propellers was from 0.5% to 4% greater than that of a 4-blade propeller and, at the high pitch settings, not appreciable inferior to that of a 2-blade propeller. It was found that the rear tandem propeller should be set at a pitch angle slightly less than that of the forward propeller to realize the condition of equal power at maximum efficiency. Under this condition the total power absorbed by the tandem propellers was from 3% to 9% more than that absorbed by the 4-blade propeller and about twice that absorbed by a 2-blade propeller.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-SR-66
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  • 79
    Publication Date: 2019-07-12
    Description: A program was undertaken to determine the J73 turbojet engine compressor stall and surge characteristics and combustor blow-out limits enc ountered during transient engine operation. Data were obtained in the form of oscillograph traces showing the time history of several engi ne parameters with changes in engine fuel flow. The data presented in this report are for step and ramp changes in fuel flow at an altitude of 45,000 feet and flight Mach numbers of 0 and 0.8.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE53F30
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  • 80
    Publication Date: 2019-07-12
    Description: A turbine blade with a porous stainless-steel shell sintered to a supporting steel strut has been fabricated for tests at the NACA by Federal-Mogul Corporation under contract from the Bureau of Aeronautics, Department of the Navy. The apparent permeability of this blade, on the average, more nearly approaches the values specified by the NAGA than did two strut-supported bronze blades in a previous investigation. Random variations of permeability in the present blade are substantialy greater than those of the bronze blades, but projected improvements in certain phases of the fabrication process are expected to reduce these variations.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE54D29
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  • 81
    Publication Date: 2019-07-12
    Description: An investigation is being conducted to determine the performance of the 12-stage axial-flow compressor of the XT-46 turbine-propeller engine. This compressor was designed to produce a pressure ratio of 9 at an adiabatic efficiency of 0.86. The design pressure ratios per stage were considerably greater than any employed in current aircraft gas-turbine engines using this type of compressor. The compressor performance was evaluated at two stations. The station near the entrance section of the combustors indicated a peak pressure ratio of 6.3 at an adiabatic efficiency of 0.63 for a corrected weight flow of 23.1 pounds per second. The other, located one blade-chord downstream of the last stator row, indicated a peak pressure ratio of 6.97 at an adiabatic efficiency of 0.81 for a corrected weight flow of 30.4 pounds per second. The difference in performance obtained at the two stations is attributed to shock waves in the vicinity of the last stator row. These shock waves and the accompanying flow choking, together with interstage circulatory flows, shift the compressor operating curves into the region where surge would normally occur. The inability of the compressor to meet design pressure ratio is probably due to boundary-layer buildup in the last stages, which cause axial velocities greater than design values that, in turn, adversely affect the angles of attack and turning angles in these blade rows.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE50E22
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  • 82
    Publication Date: 2019-07-12
    Description: An investigation of the effect of inlet pressure, corrected engine speed, and turbine temperature level on turbine-inlet gas temperature distributions was conducted on a J40-WE-6, interim J40-WE-6, and prototype J40-WE-8 turbojet engine in the altitude wind tunnel at the NAC.4 Lewis laboratory. The engines were investigated over a range of simulated pressure altitudes from 15,000 to 55,000 feet, flight Mach numbers from 0.12 to 0.64, and corrected engine speeds from 7198 to 8026 rpm, The gas temperature distribution at the turbine of the three engines over the range of operating conditions investigated was considered satisfactory from the standpoint of desired temperature distribution with one exception - the distribution for the J40-WE-6 engine indicated a trend with decreasing engine-inlet pressure for the temperature to exceed the desired in the region of the blade hub. Installation of a compressor-outlet mixer vane assembly remedied this undesirable temperature distribution, The experimental data have shown that turbine-inlet temperature distributions are influenced in the expected manner by changes in compressor-outlet pressure or mass-flow distribution and by changes in combustor hole-area distribution. The similarity between turbine-inlet and turbine-outlet temperature distribution indicated only a small shift in temperature distribution imposed by the turbine rotors. The attainable jet thrusts of the three engines were influenced in different degrees and directions by changes in temperature distributions with change in engine-inlet pressure. Inability to match the desired temperature distribution resulted, for the J40-WE-6 engine, in an 11-percent thrust loss based on an average turbine-inlet temperature of 1500 F at an engine-inlet pressure of 500 pounds per square foot absolute. Departure from the desired temperature distribution in the Slade tip region results, for the prototype J40-WE-8 engine, in an attainable thrust increase of 3 to 4 percent as compared with that obtained if tip-region temperature limitations were observed.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E52H06
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  • 83
    Publication Date: 2019-07-12
    Description: An investigation was conducted at the NACA Lewis laboratory to determine whether simulated porous gas-turbine blades fabricated by the Eaton Manufacturing Company of Cleveland, Ohio would be satisfactory with respect to coolant flow for application in gas-turbine engines. These blades simulated porous turbine blades by forcing the cooling air onto the blade surface through a large number of chordwise openings or slits between laminations of sheet metal or wire. This type of surface has a finite number of openings, whereas a porous surface has an almost infinite number of smaller openings for the coolant flow. The investigation showed that a blade made of sheet-metal laminations stacked on a support member that passed up through the coolant passage was completely unsatisfactory because of extremely poor coolant flow distribution over the blade surface. The flow distribution for two wire-wound blades was more uniform, but the pressure drop between the coolant supply pressure and the local pressure on the outside of the blades was too low by a factor ranging from 3 to 3.5 for the required coolant flow rates. The pressure drop could be increased by forcing the wires closer together during blade fabrication.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE51C13
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  • 84
    Publication Date: 2019-08-17
    Description: Theoretical investigations have shown that, because air is compressible, the pressure-drop requirements for cooling an air-cooled engine will be much greater at high altitudes and high speeds than at sea level and low speeds. Tests were conducted by the NACA to obtain some experimental confirmation of the effect of air compressibility on cooling and pressure loss of a baffled cylinder barrel and to evaluate various methods of analysis. The results reported in the present paper are regarded as preliminary to tests on single-cylinder and multi-cylinder engines. Tests were conducted over a wide range of air flows and density altitudes.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TR-783
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