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  • Aircraft Design, Testing and Performance  (172)
  • Getreide
  • AERODYNAMICS
  • Animals
  • 1945-1949  (200)
  • 1925-1929
Collection
Keywords
Years
Year
  • 1
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    Über Beziehungen zwischen der Witterung und den Ernteerträgen in Preußen (1926)
    In:  Landwirtschaftl. Jahrbuch 64:241-296
    Details
    Publication Date: 1926
    Description: Zusammenhang zwischen Niederschlag, Temperatur und Erträgen. Untersucht wurden Winterweizen, Winterroggen, Sommergerste, Sommerroggen, Kartoffeln, Futterpflanzen und Wiesen KATASTER-BESCHREIBUNG: Einfluss der Witterungsfaktoren Niederschlag und Temperatur auf die Ernteerträge KATASTER-DETAIL: Delta Nied +, dann Erträge (Halmfrüchte und Kartoffeln) + und später -; Delta T -, dann Erträge +,
    Keywords: Deutsches Reich (östl. u. westl. Provinzen, Hannover, Sachsen, Rheinland) ; 1899-1913 ; Ertrag ; Getreide ; Rangordnungsmethode ; Witterung ; Hackfrüchte
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  • 2
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    Korrelation zwischen Getreideernten und Monatssummen der Niederschläge in Baden (1926)
    In:  Diss.; Freiburg
    Details
    Publication Date: 1926
    Description: Abhängigkeit der Getreideerträge von Witterungseinflüssen mithilfe der Korrelationsmethode in 11 orographisch abgegrenzen Gebieten KATASTER-BESCHREIBUNG: Korrelation zwischen der Abweichung vom 11, bzw. 30jährigen monatlichen Mittel (April-Juli) der Niederschläge und dem Ertrag von Getreidearten (Weizen, Dinkel, Roggen, Gerste, Hafer) KATASTER-DETAIL: Nied 〉 (11, bzw. 30jährigen monatlichen Mittel von 1888-1898 und 1888-1917 im Monat Mai, je nach Region 55-158mm), dann höchste Übereinstimmung der Korrelationskoeffienten für die Ertragszunahme über alle Kulturen
    Keywords: Baden ; 1888-1898 und 1888-1917 ; Ertrag ; Getreide ; Korrelationsmethode ; Niederschlag ; Temperatur ; Witterung
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  • 3
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    Die konstitutionelle Anpassung der Kulturpflanzen an die Wasserversorgung (1949)
    In:  Zeitschrift für Pflanzenernährung, Düngung, Bodenkunde 46:176-190
    Details
    Publication Date: 1949
    Description: Zusammenhang zwischen Witterungsverlauf, Wasserbedarf und Erträgen, Aufstellung einer Konstitutionstheorie KATASTER-BESCHREIBUNG: Anpassung an den Wassermangel in der Jugend, Erziehung zur Dürreresistenz KATASTER-DETAIL: Wasserversorgung in der Jugend +, dann Wasserbedarf im Alter +;
    Keywords: Brandenburg ; 1946-48 ; Getreide ; Korrelationsmethode ; Temperatur ; Witterung
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  • 4
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    Die Abhängigkeit der Ernteerträge von den Witterungsfaktoren im Gebiet zwischen Saale, Mulde und Elbe (1928)
    In:  Vereinigten Friedrichs-Universität Halle-Wittenberg, Halle.
    Details
    Publication Date: 1928
    Description: Ertragsrelevante Korrelationen bei Winterweizen und -gerste mit der Temperatur, bei allen übrigen Kulturen war Niederschlag entscheidend KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Saalkreis, Kreis Bitterfeld, Kreis Delitzsch, Kreis Wittenberg, südl. Teil Kreis Köthen ; 1900-26 ; Kartoffeln ; Boden ; Ertrag ; Getreide ; Hafer ; Niederschlag ; Rangordnungsmethode ; Roggen ; Temperatur ; Weizen ; Witterung ; Hackfrüchte
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  • 5
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    Feldfrüchte und Witterung. (1949)
    In:  Deut. Landwirtschaflt. Presse 72:Nr. 3;6.
    Details
    Publication Date: 1949
    Description: Beziehung zwischen der Witterung und dem Ertrag verschiedener Kulturen KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Ostdeutschland ; 1900-1935 ; Boden ; Ertrag ; Getreide ; Witterung
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  • 6
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    Welchen Einfluss hat die ungünstige Witterung dieses Winters auf die Entwicklung unserer Kulturpflanzen? (1927)
    In:  Hannov. land- und forstw. Zeitg.:93-95
    Details
    Publication Date: 1927
    Description: Beschreibung der Witterungsverläufe der Winter und Empfehlungen für die Bodenbearbeitung und Bestandesführung von Winterkulturen KATASTER-BESCHREIBUNG: Einfluss der Witterung (Niederschlag und Temperatur) auf den Ertrag KATASTER-DETAIL: Delta Nied (Vorjahr) ++, dann Ertrag -; Delta Nied (Winter) +, dann Bodenfeuchte + und somit Ertrag +; Delta T (November) -, dann Ertrag -; Delta T (Winter) +, dann Ertrag +; Delta T (Frühling) +, dann Ertrag -;
    Keywords: Niedersachsen ; 1924-26 ; Insekten ; Ertrag ; Getreide ; Landwirtschaft ; Niederschlag ; Pflanzenschädling ; Roggen ; Weizen ; Düngung ; Gerste
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  • 7
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    Die Weißährigkeit des Weizens und ihre Ursachen (Ophiobolus herpotrichus u.a.) (1927)
    In:  Landwirtschaftliche Wochenschrift der Provinz Sachsen und Anhalt 29; p.668-670
    Details
    Publication Date: 1927
    Description: Der Autor führt aufgrund von Beobachtungen das Auftreten der Weißährigkeit auf Fußkrankheiten und Fusariumpilze, sowie landwirtschaftliche Praktiken zurück. In einem kleinen Abschnitt wird auch auf den Einfluß von Witterung und Bodenverhältnissen eingegangen. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Sachsen, Sachsen-Anhalt ; 1926-1927 ; Getreide ; Pflanzenkrankheit ; Weizen
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  • 8
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    Tausendkorngewicht und Witterung in den Jahren 1921 bis 1926 (1928)
    In:  Georgine, Königsberg 104 (10):65-66
    Details
    Publication Date: 1928
    Description: Einluß von Temperatur und Niederschlag in bestimmten Zeiträumen auf das Tausendkorngewicht (TKG) KATASTER-BESCHREIBUNG: Zusammenhang Niederschlag, Temperatur und Sonnenscheinstunden zum Tausendkorngewicht (Ertrag) von Weizen, Roggen und Gerste KATASTER-DETAIL: Delta T (0,48-1,9°C während der Vegetationszeit April-August über dem Mittel der Jahre 1921-26) und Delta Nied (-25- +52% vom Schossen bis zur Ernte über dem Mittel der Jahre 1921-26), dann höhreres TKG um 11,6-21,4%
    Keywords: Pommern ; 1921-1926 ; Ertrag ; Getreide ; Niederschlag ; Roggen ; Temperatur ; Weizen ; Sonnenscheindauer ; Gerste
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  • 9
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    Eine Getreidelaufkäferplage (Zabru tenebrioides) (1925)
    In:  Die kranke Pflanze 2, p. 117-119
    Details
    Publication Date: 1925
    Description: Allgemeine Beobachtungen zum Auftreten und zur Wanderung des Getreidelaufkäfers und dessen Larven; Nennung von Möglichkeiten zur Bekämpfung des Insekts KATASTER-BESCHREIBUNG: Abhängigkeit der Stärke des Auftretens von der Temperatur KATASTER-DETAIL: Delta T+, dann Auftreten der Larven +
    Keywords: Sachsen ; Beginn 20. Jahrhundert ; Insekten ; Boden ; Ertrag ; Getreide ; Landwirtschaft ; Pflanzenschädling ; Roggen ; Temperatur ; Weizen
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  • 10
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    Die Ertragsbildung in Rekorderntejahren bei Getreide (1948)
    In:  Zeitschrift für Pflanzenernährung, Düngung, Bodenkunde 40:114-129.
    Details
    Publication Date: 1948
    Description: Beschreibung der Witterung innerhalb bestimmter Zeitabschnitte bei Rekordernten KATASTER-BESCHREIBUNG: Infolge von Wachstumshemmung, durch Trockenheit in der Jugend, und Transpirationseinschränkungen, durch ausbleibende Hitzeperioden im Alter, werden die, durch den Wechsel der Jahreszeiten gegebenen, starken Unterschiede in der Versorgung der Pflanzen wesentlich gemildert KATASTER-DETAIL: Delta Nied (März-April) -, dann Erträge ++; Delta T (März) + und Delta T (April) -, dann Erträge ++; Hitzeperioden (Mai-Juni) -, dann Erträge +; Delta T (Juli-August) + und Delta Nied (Juli-August)-, dann Erträge +; Trockenperioden (Juli-August) +, dann Erträge +;
    Keywords: Ostdeutschland ; 1929-38 ; Ertrag ; Getreide ; Niederschlag ; Temperatur ; Trockenheit ; Wachstum ; Witterung
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  • 11
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    Landwirtschaftlich-klimatologische Charakteristik Anhalts als Regenschattengebietes des Harzes (1929)
    In:  Buch von: Höhne, E., (1919): Landwirtschaftlich-klimatologische Untersuchung des Gebietes zwiwchen mittlerer Saale und Pleiße und Einteilung in klimatische Unterbezirke auf Grund der Beziehungen zwischen Witterungsfaktoren und Ernteerträgen
    Details
    Publication Date: 1929
    Description: Untersuchung zur Beziehung zwischen Witterungsfaktoren und Ernteerträgen in verschiedenen Untersuchungsgebieten mittels Rangordnungsdifferenzen. Betrachtet wurden die Erträge von Roggen, Winterweizen, Sommergerste, Hafer, Sommerweizen, Zuckerrübe, Kartoffel und Erbse KATASTER-BESCHREIBUNG: Einfluss der Witterung (Niederschlag, Temperatur, Sonnenschein) auf die Erträge KATASTER-DETAIL: Delta Nied (Oktober bis März) -, dann Erträge (Roggen) +; Delta Nied (Januar) -, dann Erträge (Roggen) ++; Delta Nied (Februar) +, dann Erträge (Roggen) +; Delta Nied (Mai) +, dann Erträge (Roggen) +; Delta Nied (Mai) 〉 1,5x Mittel, dann Erträge -; Delta Sonn (Mai, im Bezirk Köthen) +, dann Erträge (Roggen) -; Delta Nied (Januar, März, April) -, dann Erträge (Sommergerste) +; Delta Nied (Februar, Mai bis Ernte) +, dann Erträge (Sommergerste) +; Delta Nied (Mai) +, dann Erträge (Sommergerste) ++; Köthen (Nied 15-30mm im März), (Delta T- im April/Juni, besonders im Mai), dann Winterweizenertrag++ (weitere Informationen zu den weiteren landwirtschaftlicher Kulturpflanzen und Regionen: siehe Artikel)
    Keywords: Sachsen und Thüringen ; 1899-1926 ; Boden ; Ertrag ; Getreide ; Klima ; Korrelationsmethode ; Landwirtschaft ; Niederschlag ; Roggen ; Temperatur ; Weizen ; Globalstrahlung ; Hackfrüchte
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  • 12
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    Versuche über die Ausnützung steigender Stickstoffgaben durch verschiedene Hafersorten, IV Versuche mit Hafer (1929)
    In:  Zeitschrift für Pflanzenernährung, Düngung, Bodenkunde 8:425-458
    Details
    Publication Date: 1929
    Description: Auswirkungen über gestaffelte Stickstoff-Düngung auf den Ertrag von Weizen, Gerste, Roggen und Hafer. Angaben zu Temperatur und Niederschlag während der Vegetationszeit, Hinweise auf Zusammenhang zwischen Witterung und Ertrag und Wirkung der Düngung, Bedeutung eines längeren Zeitraums für die Beobachtungen KATASTER-BESCHREIBUNG: Einfluss von Niederschlag und Temperatur auf den Ertrag von Hafer KATASTER-DETAIL: Delta Nied (nach der Saat) +, dann t(Aufgang) - (später); Delta Nied (Ende des Wachstum) -, dann Erträge (Hafer) -; Delta T (20 Tage nach dem Aufgang) +: T 〉 11°C, dann Ertrag (Hafer) -;
    Keywords: Bayern ; 1924-28 ; Ertrag ; Getreide ; Hafer ; Niederschlag ; Roggen ; Temperatur ; Weizen ; Düngung ; Gerste
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  • 13
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    Beobachtungen über die diesjährige Dürre (1925)
    In:  Pflanzenbau, Halbmonatsschrift für Saatwesen, Anbau und Pflege der Kulturpflanzen. II. Jahrgang 1925/26 S.106-108.
    Details
    Publication Date: 1925
    Description: Einfluss der Trockenheit im Sommer auf Getreide, Leguminosen und Zuckerrüben KATASTER-BESCHREIBUNG: Einfluss der Temperatur und des Niederschlags auf den Ertrag KATASTER-DETAIL: Delta T (Vorjahreswinter) + und Delta Nied (Sommer) -, dann Pflanzenschädlinge (Erbsenwickler, Fritfliege) +; Delta T (Vorjahreswinter) + und Delta Nied (Sommer) -, dann Ertrag (Kartoffeln) +; Delta T (Vorjahreswinter) + und Delta Nied (Sommer) -, dann Ertrag (Sommergerste) -;
    Keywords: Pommern ; 1925 ; Ertrag ; Getreide ; Niederschlag ; Trockenheit
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  • 14
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    Die Beziehung zwischen Bodentemperatur und Lufttemperatur und ihrem Einfluss auf den Ernteertrag. (1927)
    In:  Fortschr. Landw. 2:205-212.
    Details
    Publication Date: 1927
    Description: Untersuchungen über die Gründe für die schlechte Getreideernte im Donau-Einzugsgebiet des Jahres 1924, Zusammenhang zwischen der Luft- und Bodentemperatur, dem Pflanzenwachtum und dem Ertrag KATASTER-BESCHREIBUNG: Korn-Stroh-Verhältnis wird beeinflusst von dem Verhältnis der Boden- zur Lufttemperatur, KATASTER-DETAIL: Delta T (Diff. Boden zu Luft im Mai) 〈 0, dann ertragsrelevant
    Keywords: Bayern ; 1913-15, 1924-26 ; Ertrag ; Getreide ; Temperatur ; Frost
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  • 15
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    Einfluss der Witterungs-Erscheinungen auf die Erträge unserer Kulturpflanzen. (1928)
    In:  Deut. Landwirtschaflt. Presse 55:94-95.
    Details
    Publication Date: 1928
    Description: Übersicht über die Literatur zum Einfluss des Wetters auf die Kulturpflanzen KATASTER-BESCHREIBUNG: Milder und trockener Winter wirkt positiv auf die Weizenerträge, kalter und niederschlagsreicher Winter eher negativ, Betrachung für Norddeutschland KATASTER-DETAIL:
    Keywords: Deutschland ; 1900-1926 ; Kartoffeln ; Ertrag ; Getreide ; Hafer ; Landwirtschaft ; Niederschlag ; Roggen ; Temperatur ; Trockenheit ; Witterung ; Gerste
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  • 16
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    Biometrical studies on the variation of physiologic forms of Puccinia graminis tritici and the effects of ecological factors on the susceptibility of wheat varieties (1928)
    In:  Phytopathology 18, No.1, p. 7-123
    Details
    Publication Date: 1928
    Description: Ergebnisse 5-jähriger Freilandversuche und 9-jähriger Laborversuche zu den Zusammenhängen zwischen klimatischen und anderen Umweltfaktoren und dem Auftreten verschiedener physiologischer Formen des Schwarzrostes an unterschiedlichen Weizensorten in den USA und Kanada. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: USA, Kanada ; 1919-1923 ; Getreide ; Pflanzenkrankheit ; Weizen
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  • 17
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    Zwei beachtenswerte Erscheinungen des Jahres 1926 (1926)
    In:  Hess. Landw. Zeitschr. 96, p.346
    Details
    Publication Date: 1926
    Description: Der Autor äußert die Vermutung, daß strenge Winter den Rostbefall vermindern und erwähnt das starke Befallsjahr 1926. Er klagt über ein noch zu geringes Wissen über die beeinflussenden Klimafaktoren. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Wetterau, Hessen ; 1926 ; Getreide ; Pflanzenkrankheit
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  • 18
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    Frittfliegenbefall in den Ähren der Wintergerste (1949)
    In:  Neue Mitt. Landwirtsch. 4; p.130-132
    Details
    Publication Date: 1949
    Description: Der Autor beschreibt den Lebenszyklus der Frittfliege und dokumentiert das Auftreten des Schädlings in vergangenen Jahren. In einem sehr kurzen Absatz wird das Auftreten des schädlings mit warmem Frühlingswetter und der Sonnenscheindauer bzw. der Temperatur im Mai in Verbindung gebracht. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland ; 1948 ; Getreide ; Pflanzenschädling ; Gerste
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  • 19
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    Massenauftreten der gelben Halmfliege in Schleswig-Holstein (1926)
    In:  Nachrichtenblatt für den deutschen Pflanzenschutzdienst, Jahrgang 6, Nr. 4, p. 27
    Details
    Publication Date: 1926
    Description: Beobachtungen zum Auftreten der gelben Halmfliege in Schleswig-Holstein und deren Auswirkungen auf bestimmte Getreidearten (Sommerweizen und Sommergerste) KATASTER-BESCHREIBUNG: Einfluss der Witterung auf das Auftreten der Fliege KATASTER-DETAIL: Delta Nied +, dann Sommerflug -
    Keywords: Schleswig-Holstein ; 1926 ; Insekten ; Anbautermine ; Getreide ; Landwirtschaft ; Niederschlag ; Pflanzenschädling ; Weizen ; Gerste
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  • 20
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    Korrelaionen zwischen Witterung und Ernteertrag (1945)
    In:  Verh. Schweiz. Naturforsch. Ges. Freiburg, 135-137
    Details
    Publication Date: 1945
    Description: Beziehung von Temperatur und Niederschlag zum Ertrag von Getreide KATASTER-BESCHREIBUNG: Anzahl der Tage mit Niederschlag im Juli (Korrelationskoeffizient =-0.6) hat höchste Korrelation bei Winterweizen KATASTER-DETAIL:
    Keywords: Schweiz ; 1942-44 ; Ertrag ; Getreide ; Korrelationsmethode ; Niederschlag ; Temperatur ; Weizen
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  • 21
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    Untersuchungen über Schadgebiet und Umweltfaktoren einiger landwirtschaftlicher Schädlinge in Deutschland auf Grund statistischer Unterlagen (1929)
    In:  Zeitschrift für angewandte Entomologie, Nov. 1929, p.565-627
    Details
    Publication Date: 1929
    Description: Einfluß der Witterung auf das Auftreten von Rübenaaskäfer, Zwergzikade, Ackerschnecke, Weizenhalmfliege, Getreideblumenfliege KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland, regional aufgelöst ; 1893-1927 ; Getreide ; Pflanzenschädling ; Hackfrüchte
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  • 22
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    Untersuchungen über die Beziehungen von Ernte- und Klimaschwankungen in der Wetterau (1948)
    In:  Diss., Gießen
    Details
    Publication Date: 1948
    Description: Rangordung der Ertrage nach Gruppen und Korrelationen zu Witterungsfaktoren; Ertragsaufzeichenungen von Betrieben und Klimaaufzeichnungen aus stat. Berichten der Wetterau KATASTER-BESCHREIBUNG: Ertragsrückgänge bei Wassermangel,Relation zwischen Ertrag und Temperatur/Luftfeuchte insb. bei Hackfrüchten KATASTER-DETAIL: Delta Nied (Herbst) -, Delta T (Winter) +, Delta T (Frühjahr) +, Delta Nied (Mai) +, Delta T (letzte Monate des Ausreifens) -, Delta Sonn (letzte Monate des Ausreifens) +, dann Ertrag +;
    Keywords: Wetterau, Hessen ; 1924-1938 ; Ertrag ; Getreide ; Niederschlag ; Temperatur ; Hackfrüchte
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  • 23
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    Erfahrungen über den diesjährigen Rostbefall beim Winterweizen und einige Vorbeugungsmaßnahmen (1926)
    In:  Jllustr. Landw. Zeitg. 46; p.551-552
    Details
    Publication Date: 1926
    Description: Schilderung des Rostbefalls (insbesondere Gelbrost)in der Region Kassel im Jahre 1926. Der Autor beklagt das bisher fehlende Wissen der Wissenschaftler und präsentiert eine Umfrage unter Landwirten zu den Einflußfaktoren (u.a. klimatische) auf den Rostbefall. Zudem werden Vorbeugungsmaßnahmen vorgestellt. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Kassel ; 1926 ; Getreide ; Pflanzenkrankheit ; Weizen
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  • 24
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    Einfluß der Witterung auf die Entwicklung und den Gesundheitszustand der landwirtschaftlichen Kulturpflanzen im Jahre 1926 (1926)
    In:  Prakt. Blätter. Bayer. Landesanst. Pflanzenbau und Schutz 4 (5): 103-111
    Details
    Publication Date: 1926
    Description: Beobachtungen zu den Auswirkungen der Witterung im Jahr 1926 auf Getreide, Futterpflanzen und Kartoffeln sowie ihrer Schädigungen durch verschiedene Schaderreger, wie z.B. Roste, Fusarien, Phytophthora, etc. KATASTER-BESCHREIBUNG: Einfluss der Witterung (Temperatur, Niederschlag, Sonnenschein) auf den Ertrag KATASTER-DETAIL: Delta T (Februar) +, dann Auswinterungsschäden +; Delta T (März, April) + und Delta Nied (März) +, dann Entwicklung + (früher); Delta T (Mai, Juni) -: T 〈 0 °C (Frost), dann Kälteschäden +; Delta Sonn (Juni, Juli) -, dann Entwicklung -; Delta T (Frühjahr) +, dann Ertrag (Wintergetreide - außer Winterroggen) +; Delta T (Mai) - : T 〈 0 °C, dann Wachstum (Winterweizen) - und Auftreten von Gelbrost +, dadurch Ertrag (Winterweizen) -; Delta T(Frühjahr) +, dann Saat + (früher) und Entwicklung +, dadurch Ertrag (Sommergetreide) +; Delta Nied (Sommer) +, dann Entwicklung (Rüben) +; Delta Nied (Sommer) + und Delta T (Sommer) -, dann Entwicklung (Pferdebohnen) -; Delta Nied (Sommer) + und Delta T (Sommer) -, dann Entwicklung (Kartoffeln) -;
    Keywords: Bayern ; 1926 ; Kartoffeln ; Getreide ; Pflanzenkrankheit ; Pflanzenschädling ; Hackfrüchte
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  • 25
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    Witterung und Gerstenerträge (1928)
    In:  Landw. Wochenschrift für die Provinz Sachsen und Anhalt, Hallle 18:428ff.
    Details
    Publication Date: 1928
    Description: Zusammenhang Witterung in Monaten und Gerstenertrag KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Sachsen und Anhalt ; 1920 ; Ertrag ; Getreide ; Landwirtschaft ; Niederschlag ; Temperatur ; Witterung
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  • 26
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    Der Einfluß des Klimas auf die Erntebeschaffenheit des Getreides (1925)
    In:  Mitt. Deut. Landw. Gesell. 40:950-55.
    Details
    Publication Date: 1925
    Description: Zusammenhang zwischen Weizenqualität und den klimatischen Verhältnissen, Schwerpunkt auf die Physiologie des Samens und Qualität (Backfähigkeit) KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Europa ; letzten100 Jahre ; Ertrag ; Getreide ; Klima ; Niederschlag ; Temperatur ; Weizen
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  • 27
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    Untersuchungen über Beziehungen zwischen Witterung und Ernteertrag in der Landwirtschaft (1928)
    In:  Diss., Hohenheim.
    Details
    Publication Date: 1928
    Description: Beziehung zwischen Witterung (unterteilt in einzelne Monate) und Ertragshöhe mithilfe der Rangordnungs- und der Korrelationsmethode KATASTER-BESCHREIBUNG: Einfluss der Witterung (Temperatur, Niederschlag, Sonnenscheindauer) auf den Ertrag von Winterweizen, Sommerweizen, Sommergerste, Wintergerste, Hafer und Runkelrüben auf dem Versuchsfeld (wasserundurchlässiger Boden) KATASTER-DETAIL: Delta Sonn (Oktober bis November)+, dann Erträge (Winterweizen) +; Delta Sonn (Dezember bis März)+, dann Erträge (Winterweizen) -; Delta Sonn (April) -, dann Erträge (Winterweizen) +; Delta Nied (April) +, dann Erträge (Winterweizen) +; Delta Nied (Mai, Juni und Juli) -, dann Erträge (Winterweizen) +; Delta Nied (August bis Oktober) +, dann Erträge (Winterweizen) +; Delta T (April) -, dann Erträge (Winterweizen) +; (Details sowie Informationen für Sommerweizen, Sommergerste, Wintergerste, Hafer und Runkelrüben siehe Artikel)
    Keywords: Hohenheim (Baden-Württemberg) ; 1914-25 ; Ertrag ; Getreide ; Hafer ; Klima ; Korrelationsmethode ; Niederschlag ; Rangordnungsmethode ; Temperatur ; Weizen ; Witterung ; Hackfrüchte
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  • 28
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    Die "kritischen Zeiten" und das "ökologische Optimum" der Witterungsfaktoren, ein Mittel zur Bestimmung der Ernteertäge (1926)
    In:  Zeitschrift für Acker- und Pflanzenbau 3:330-334.
    Details
    Publication Date: 1926
    Description: Angabe von Niederschlagsmengen und Durchschnittstemperaturen für das ökologische Optimum bestimmter Sorten, kritische Zeiten (vor und nach der Blüte) sind hierfür entscheidend KATASTER-BESCHREIBUNG: Einfluss von Wasser und Wärme, bzw. Niederschlag und Temperatur auf den Ertrag KATASTER-DETAIL: Roggen, Weizen: Delta Nied (Beginn Blütezeit)-, dann Ertrag +; Hafer, Gerste, Kartoffel: Delta T (Beginn der Blüte) -, dann Ertrag +; Bohne: Delta T (gesamte Wachstumszeit)+ und Delta Nied (gesamte Wachstumszeit) +, dann Ertrag +
    Keywords: Göttingen ; 1901-22 ; Kartoffeln ; Ertrag ; Getreide ; Hafer ; Klima ; Korrelationsmethode ; Niederschlag ; Roggen ; Temperatur ; Weizen ; Witterung ; Hackfrüchte ; Erbsen
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  • 29
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    Zwei verbreitete Weizenschädlinge dieses Jahres (1925)
    In:  Sächs. Landw. Zeitschr. 73, p.614
    Details
    Publication Date: 1925
    Description: Beschreibung der Schäden und Erscheinungsformen des Weizenhalmtöters und der Weizenhalmfliege im Jahre 1926 in Sachsen. Nur bedingte Verknüpfung mit klimatischen Parametern. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Sachsen ; 1926 ; Getreide ; Pflanzenschädling ; Weizen
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  • 30
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    Die Schwankungen der barometrischen Hochlagen über Mitteleuropa und ihr Einfluß auf die Ernteerträge in Deutschland (1929)
    In:  Kühn-Archiv, Berlin, XX, Seite 7-129
    Details
    Publication Date: 1929
    Description: Lage der Hochs nördlich und südlich des 50. Breitengrades und ihre Bedeutung für die Witterung und Ernteerträge in Mitteldeutschland KATASTER-BESCHREIBUNG: KATASTER-DETAIL: Tmit+ (Janurar, Februar, März, Mai und Dezember) durch Abnahem der barometrischen Nordlagen Tmit- (August, September) durch Zunahme der barometrischen Nordlagen Nied+ (Janurar, Apri,, Mai, August, September, Dezember) durch Abnahmen der barometrischen Nordlagen (entspricht Zunahmen der Südlagen!) Nied- (Februar, März, Oktober und November) durch Abnahmen der barometrischen Nordlagen (entspricht Zunahmen der Südlagen!)
    Keywords: Deutschland ; 1900-1925 ; Luftfeuchte ; Ertrag ; Getreide ; Landwirtschaft ; Niederschlag ; Temperatur ; Trockenheit ; Witterung ; Sonnenscheindauer
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  • 31
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    Insektenschädigungen am Getreide (1925)
    In:  Georgine, Jahrgang 102, Nr. 68, p. 806-807
    Details
    Publication Date: 1925
    Description: Biologie und Bekämpfung von Fritfliege, Getreideblumenfliege, scheckige oder gelbe Halmfliege, Weizenfliege, Hessenfliege KATASTER-BESCHREIBUNG: Einfluss der Witterung (Temperatur, Niederschlag und Wind) auf die Schädlinge KATASTER-DETAIL: Delta T (Winter) +, Anzahl Maden der Halmfliege +; Delta Nied (September) + und Delta Wind (September) +, dann Hessenfliege -
    Keywords: Deutschland ; 1903-1925 ; Insekten ; Anbautermine ; Boden ; Ertrag ; Getreide ; Hafer ; Niederschlag ; Pflanzenschädling ; Temperatur ; Vegetationsperiode ; Weizen ; Wind ; Witterung ; Düngung ; Gerste
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  • 32
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    Zum Auftreten des Gelbrostes des Weizens (1926)
    In:  Nassauer Land 108, p. 185
    Details
    Publication Date: 1926
    Description: Beobachtungen zum Gelbrostbefall von Weizen, Roggen und Gerste KATASTER-BESCHREIBUNG: - KATASTER-DETAIL: -
    Keywords: Deutschland ; 1926 ; Infektionskrankheiten ; Getreide ; Pflanzenkrankheit ; Roggen ; Weizen ; Gerste
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  • 33
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    Die Ertragsbildung in Rekorderntejahren bei Getreide (1948)
    In:  Zeitschr. Pflanzenernährung, Düngung, Bodenkunde 40: 114-129
    Details
    Publication Date: 1948
    Description: Vergleich der Witterungsfaktoren in den Rekorderntejahren 1933 und 1938 von März bis August KATASTER-BESCHREIBUNG: Identifizierung der wichtigen Zeitabschnitte März-April und Juli-August,hier hohe Temperaturen für Rekordernten unabdingbar KATASTER-DETAIL: Delta Nied - (Frühjahr), dann Ertrag +; Nied (Normal und gleichmäßig), im Mai Delta Nied+, dann Ertrag+
    Keywords: Berlin, Brandenburg ; 1933-1938 ; Ertrag ; Getreide ; Niederschlag ; Temperatur ; Trockenheit
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  • 34
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    NACA Conference on Boundary Layers. A compilation of the papers presented (1947)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Keywords: AERODYNAMICS
    Format: text
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  • 35
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    Lattice arrangements for rapid convergence (1926)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A simple, systematic, optimized vortex-lattice approach is developed for application to lifting-surface problems. It affords a significant reduction in computational costs when compared to current methods. Extensive numerical experiments have been carried out on a wide variety of configurations, including wings with camber and single or multiple flaps, as well as high-lift jetflap systems. Rapid convergence as the number of spanwise or chordwise lattices are increased is assured, along with accurate answers. The results from this model should be useful not only in preliminary aircraft design but also, for example, as input for wake vortex roll-up studies and transonic flow calculations.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Vortex-Lattice Utilization; p 325-342
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  • 36
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    Some considerations of aerodynamic heating (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA: Univ. Conf. on Aerodyn.; p 399-411
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  • 37
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    The use of conincal and cylindrical fields in supersonic wing theory (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA. Langley Aeron. Lab. NACA: Univ. Conf. on Aerodyn.; p 341-353
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  • 38
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    Summary of NACA submerged-inlet investigations (1947)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 49-52
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  • 39
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    Lift and drag characteristics of a wing with several angles of sweep at high subsonic speeds (1947)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA. Ames Aeron. Lab. NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 21-28
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  • 40
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    Investigation of side inlets at supersonic speeds (1947)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 53-57
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  • 41
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    A review of recent information relating to the drag rise of airplanes (1947)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA. Ames Aeron. Lab. NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 3-13
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  • 42
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    Air inlets (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA: Univ. Conf. on Aerodyn.; p 307-322
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  • 43
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    Characteristics of wing sections at transonic speeds (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA: Univ. Conf. on Aerodyn.; p 127-149
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  • 44
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    A review of approximate methods in subsonic compressible flow (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA: Univ. Conf. on Aerodyn.; p 29-46
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  • 45
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    The use of source and sink concepts in the calculation of wing characteristics at supersonic speeds (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA: Univ. Conf. on Aerodyn.; p 355-365
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  • 46
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    Prediction of Wing Characteristics (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA: Univ. Conf. on Aerodyn.; p 151-166
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  • 47
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    Characteristics of wing sections at subcritical speeds (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA: Univ. Conf. on Aerodyn.; p 109-125
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  • 48
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    Two-dimensional supersonic wing theory (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA. Langley Aeron. Lab. NACA: Univ. Conf. on Aerodyn.; p 325-340
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  • 49
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    Prediction of the aerodynamic characteristics of wings of arbitrary plan form (1947)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 95-100
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  • 50
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    Nose inlets (1947)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA. Ames Aeron. Lab. NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 43-48
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  • 51
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    Airfoil section characteristics at high subsonic speeds (1947)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA Conf. on Aerodyn. Probl. of Transonic Airplane Design; p 15-20
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  • 52
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    A survey of methods for the calculation of flow around bodies of revolution at supersonic speeds (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA: Univ. Conf. on Aerodyn.; p 377-395
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  • 53
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    Unsteady lift in high-speed flight (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA. Langley Aeron. Lab. NACA: Univ. Conf. on Aerodyn.; p 367-376
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  • 54
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    Maximum-lift and stalling characteristics of wings (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA: Univ. Conf. on Aerodyn.; p 167-183
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  • 55
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    Stability of the laminar boundary layer (1948)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: AERODYNAMICS
    Type: NACA: Univ. Conf. on Aerodyn.; p 3-26
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  • 56
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    The Characteristics of the N.A.C.A 97, Clark Y, and N.A.C.A. M6 Airfoils with Particular Reference to the Angle of Attack (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-270
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  • 57
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    The Light Airplane (1925)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report begins with a review and analysis of the work being done to develop light airplanes in the U.S. and abroad. A technical discussion of the construction and innovations in light airplanes is then presented.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-311
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  • 58
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    Determination of Aircraft Antenna Loads Produced by Natural Icing Conditions (1948)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A flight investigation was made to determine the effect of distance flown in the icing region, antenna length, and antenna angle on the tension occurring in aircraft antennae while in regions of aircraft icing. The experimental antennas were of lengths ranging from 15 to 43 feet and were placed at angles of 0 deg to 64 deg with the airplane thrust axis. Distances up to 256 miles were flown in diverse icing conditions at true airspeeds from 157 to 214 miles per hour and pressure altitudes at which icing conditions were encountered. The results indicate that: The effect of ice formation on antenna tension increased with the angle of the antennas with the longitudinal axis of the airplane. The maximum tension for antennae having angles from 0 deg to 15 deg was 68 pounds, whereas the maximum tension for antennas having angles of 44 deg and 64 deg was 274 and 438 pounds, respectively.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E7H26a
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  • 59
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    A Method for Calculating the Heat Required for Windshield Thermal Ice Prevention Based on Extensive Flight Tests in Natural Icing Conditions (1947)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An equation is presented for calculating the heat flow required from the surface of an internally heated windshield in order to prevent the formation of ice accretions during flight in specified icing conditions. To ascertain the validity of the equation, comparison is made between calculated values of the heat required and measured values obtained for test windshields in actual flights in icing conditions. The test windshields were internally heated and provided data applicable to two common types of windshield configurations; namely the V-type and the type installed flush with the fuselage contours. These windshields were installed on a twin-engine cargo airplane and the icing flights were conducted over a large area of the United States during the winters of 1945-46 and 1946-47. In addition to the internally heated windshield investigation, some test data were obtained for a windshield ice-prevention system in which heated air was discharged into the windshield boundary layer. The general conclusions resulting from this investigation are as follows: 1) The amount of heat required for the prevention of ice accretions on both flush- and V-type windshields during flight in specified icing conditions can be calculated with a degree of accuracy suitable for design purposes. 2) A heat flow of 2000 to 2500 Btu per hour per square foot is required for complete and continuous protection of a V-type windshield in fight at speeds up to 300 miles per hour in a moderate cumulus icing condition. For the same degree of protection and the same speed range, a value of 1000 Btu per hour per square foot suffices in a moderate stratus icing condition. 3) A heat supply of 1000 Btu per hour per square foot is adequate for a flush windshield located well aft of the fuselage stagnation region, at speeds up to 300 miles per hour, for flight in both stratus and moderate cumulus icing conditions. 4) The external air discharge system of windshield thermal ice prevention is thermally inefficient and requires a heat supply approximately 20 times that required for an internal system having the same performance.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-1434
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  • 60
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    Static-thrust Investigation of Full-scale PV-2 Helicopter Rotors Having NACA 0012.6 and 23012.6 Airfoil Sections (1946)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted to compare the performance of two 25-ft-diam rotors which had identical dimensions and were similar in construction but different in blade airfoil-sections. Tests were conducted at indicated blade pitch angles from 3 degrees to 11.5 degrees and rotor speeds of 200, 290, and 371 rpm. The 23012.6 rotor required 2 percent less power to hover than the 0012.6. At thrust coefficients above design, the performance of the 23012.6 became better than the 0012.6 rotor.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-749 , NACA-MR-L6D24
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  • 61
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    Resistance Tests of Models of Three Flying-boat Hulls with a Length-beam Ratio of 10.5 (1945)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-79 , NACA-ARR-L5G19
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  • 62
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    Correlation of Mixture Temperature Data Obtained from Bare Intake-manifold Thermocouples (1946)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A relatively simple equation has been found to express with fair accuracy, variation in manifold-charge temperature with charge in engine operating conditions. This equation and associated curves have been checked by multi cylinder-engine data, both test stand and flight, over a wide range of operating conditions. Average mixture temperatures, predicted by the equations of this report, agree reasonably well with results within the same range of carburetor-air temperatures from laboratories and test stands other than the NACA.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-E-273 , NACA-MR-E5L03
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  • 63
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    Effect of Compressibility on the Pressure and Forces Acting on a Modified NACA 65,3-019 Airfoil Having A 0.20-Chord Flap (1946)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation has been conducted in the Langley rectangular high-speed tunnel to determine the effect of compressibility on the pressure distribution for a modified NACA 65,3-019 airfoil having a 0.20-chord flap. The investigation was made for an angle-of-attack range extending from -2 to 12 deg at .20 flap deflections from 0 to -12 deg. Test data were obtained for Mach numbers from 0.28 to approximately 0.74. The results show that the effectiveness of the trailing-edge-type control surface rapidly decreased and approached zero as the Mach number increased above the critical value.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-76 , NACA-ACR-L5G31A
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  • 64
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    Wind-Tunnel Investigation of a Rectangular NACA 2212 Airfoil with Semispan Ailerons and with Nonperforated, Balanced Double Split Flaps for Use as Aerodynamic Brakes (1945)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flat-plate flaps with no wing cutouts and flaps having Clark Y sections with corresponding cutouts made in wing were tested for various flap deflections, chord-wise locations, and gaps between flaps and airfoil contour. The drag was slightly lower for wing with airfoil section flaps. Satisfactory aileron effectiveness was obtained with flap gap of 20% wing chord and flap-nose location of 80 percent wing chord behind leading edge. Airflow was smooth and buffeting negligible.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-56 , NACA-ARR-L5B17
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  • 65
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    Laboratory Investigation of Ice Formation and Elimination in the Induction System of a Large Twin-engine Cargo Aircraft (1947)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The icing characteristics, the de-icing rate with hot air, and the effect of impact ice on fuel metering and mixture distribution have been determined in a laboratory investigation of that part of the engine induction system consisting of a three-barrel injection-type carburetor and a supercharger housing with spinner-type fuel injection from an 18-cylinder radial engine used on a large twin-engine cargo airplane. The induction system remained ice-free at carburetor-air temperatures above 36 F regardless of the moisture content of the air. Between carburetor-air temperatures of 32 F and 36 F with humidity ratios in excess of saturation, serious throttling ice formed in the carburetor because of expansion cooling of the air; at carburetor-air temperatures below 32 F with humidity ratios in excess of saturation, serious impact-ice formations occurred, Spinner-type fuel injection at the entrance to the supercharger and heating of the supercharger-inlet elbow and the guide vanes by the warn oil in the rear engine housing are design features that proved effective in eliminating fuel-evaporation icing and minimized the formation of throttling ice below the carburetor. Air-flow recovery time with fixed throttle was rapidly reduced as the inlet -air wet -bulb temperature was increased to 55 F; further temperature increase produced negligible improvement in recovery time. Larger ice formations and lower icing temperatures increased the time required to restore proper air flow at a given wet-bulb temperature. Impact-ice formations on the entrance screen and the top of the carburetor reduced the over-all fuel-air ratio and increased the spread between the over-all ratio and the fuel-air ratio of the individual cylinders. The normal spread of fuel-air ratio was increased from 0.020 to 0.028 when the left quarter of the entrance screen was blocked in a manner simulating the blocking resulting from ice formations released from upstream duct walls during hot-air de-icing.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-1427
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  • 66
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    Wind Tunnel Pressure Distribution Tests on a Series of Biplane Wing Models. Part III Effects of Charges in Various Combinations of Stagger, Gap, Sweepback, and Decalage (1929)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This preliminary report furnishes information on the changes in the forces on each wing of a biplane cellule for various combinations of stagger and gap, stagger and sweepback, stagger and decalage, and gap and decalage. The data were obtained from pressure distribution tests made in the atmospheric wind tunnel of the Langley Memorial Aeronautical Laboratory. Since each test was carried up to 90deg angle of attack, the results may be used in the study of stalled flight and of spinning as well as in the structural design of biplane wings.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-330
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  • 67
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    The Calculation of the Heat Required for Wing Thermal Ice Prevention in Specified Icing Conditions (1947)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flight tests were made in natural icing conditions with two 8-ft-chord heated airfoils of different sections. Measurements of meteorological variables conducive to ice formation were made simultaneously with the procurement of airfoil thermal data. The extent of knowledge on the meteorology of icing, the impingement of water drops on airfoil surfaces, and the processes of heat transfer and evaporation from a wetted airfoil surface have been increased to a point where the design of heated wings on a fundamental, wet-air basis now can be undertaken with reasonable certainty.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-1472
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  • 68
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    Effects of Wing and Nacelle Modifications on Drag and Wake Characteristics of a Bomber-Type Airplane Model (1945)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation of a model of a large four-engine bomber was conducted in the Langley 19-f'oot pressure tunnel to determine the effects of several wing and nacelle modifications on drag characteristics and air flow characteristics at the tail. Leading-edge gloves, trailing-edge extensions, and modified nacelle afterbodies were tested individual ly and in combination. The effects of the various modifications were determined by force tests, tuft observations, and turbulence s1ITveys in the region of the tail. Tests were made with fixed and natural transition on the wing and with propellers operating and propellers off. Most of the tests were con- ducted at a Reynolds number of approximately 2.6 x 106. The results indicated that application of certain of the modifications provided worth-while improvements in the characteristics or the model. The flow over the wing and flaps was improved, the drag was reduced, and the turbulence in the region of the tail was reduced. Trailing-edge extensions were the most effective individual modification in improving the flow over the wing with wing flaps neutral, cowl and intercooler flaps clos ed. Modified nacelle afterbodies were the most effectiv8 individual edification in reducing drag with either fixed or natural transition on the wing; however, trailin6-edge extensions were slightly more effective with fixed transition. Combinations of either leading or trailing-edge extensions and modified afterbodies were more effective than either modification alone. With cowl and intercooler flaps open, trailing-edge extensions with modified afterbodies provided substantial improvement in flow and drag characteristics. With wing flaps deflected, enclosing the flap behind the inboard nacelle within an extended afterbody or cutting the flaps at the nacelle appeared. to be the most promising methods of improving the f low over the flaps and the tail. Although the results of hot-wire-anenometer surveys were not conclusive in regard to buffeting characteristics, the modifications did educe the turbulence at the tail with wing flaps both neutral and deflected. The modifications, as a rule, were favorable to maximum lift. Appreciable reductions in longitudinal stability of the model were caused by addition of leading -edge gloves and tr ailing -edge extensions.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-114 , NACA-ARR-L5J05
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  • 69
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    Flight Measurements to Determine Effect of a Spring-Loaded Tab on Longitudinal Stability of an Airplane (1946)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In conjunction with a program of research on the general problem of stability of airplanes in the climbing condition, tests have been made of a spring-loaded tb which. is referred to as a ?springy tab,? installed on the elevator of a low-wing scout bomber. The tab was arranged to deflect upward with decrease in speed which caused an increase in the pull force required to trim at low speeds and thereby increased the stick-free static longitudinal stability of the airplane. It was found that the springy tab would increase the stick-free stability in all flight conditions, would reduce the danger of inadvertent stalling because of the definite pull force required to stall the airplane with power on, would reduce the effect of center-of-gravity position on stick-free static stability, and would have little effect on the elevator stick forces in accelerated f11ght. Another advantage of the springy tab is that it might be used to provide almost any desired variation of elevator stick force with speed by adjusting the tab hinge-moment characteristics and the variation of spring moment with tab deflection. Unlike the bungee and the bobweight, the springy tab would provide stick-free static stability without requiring a pull force to hold the stick back while taxying. A device similar to the springy tab may be used on the rudder or ailerons to eliminate undesirable trim-force variations with speed.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-210 , NACA-ARR-L5I20
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  • 70
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    Data for Design of Entrance Vanes from Two-Dimensional Tests of Airfoils in Cascade (1945)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As a part of a program of the NACA directed toward increasing the efficiency of compressors and turbines, data were obtained for application to the design of entrance vanes for axfax-flow compressors or turbines. A series of blower-blade sections with relatively high critical speeds have been developed for turning air efficiently from 0 deg to 80 deg starting with an axial direction. Tests were made of five NACA 65-series blower blades (modified NACA 65(216)-010 airfoils) and of four experimentally designed blower blades in a stationary cascade at low Mach numbers. The turning effectiveness and the pressure distributions of these blade sections at various angles of attack were evaluated over a range of solidities near 1. Entrance-vane design charts are presented that give a blade section and angle of attack for any desired turning angle. The blades thus obtained operate with peak-free pressure distributions. Approximate critical Mach numbers were calculated from the pressure distributions.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-L-188 , NACA-ACR-L5G18
    Format: application/pdf
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  • 71
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    Appreciation and Prediction of Flying Qualities (1949)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The material given in this report summarizes some of the results of recent research that will aid the designers of an airplane in selecting or modifying a configuration to provide satisfactory stability and control characteristics. The requirements of the NACA for satisfactory flying qualities, which specify the important stability and control characteristics of an airplane from the pilot's standpoint, are used as the main topics of the report. A discussion is given of the reasons for the requirements, of the factors involved in obtaining satisfactory flying qualities, and of the methods used in predicting the stability and control characteristics of an airplane. The material is based on lecture notes for a training course for research workers engaged in airplane stability and control investigations.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TR-927
    Format: application/pdf
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  • 72
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    Junkers Airplane "G 24" : All-metal Commercial Airplane (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The G 24 is a commercial airplane with three engines and a monoplane wing. It is known for it's all metal construction and stabilizers.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-AC-47
    Format: application/pdf
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  • 73
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    Investigation of Aerodynamic and Icing Characteristics of Recessed Fuel-Vent Configurations (1949)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation has been conducted in the NACA Cleveland icing research tunnel to determine the aerodynamic and icing characteristics of several recessed fuel-vent configurations. The vents were investigated aerodynamically to obtain vent-tube pressures and pressure distributions on the ramp surface as functions of tunnel-air velocity and angle of attack. Icing investigations were made to determine the vent-tube pressure losses for several icing conditions at tunnel-air velocities ranging from 220 to 440 feet per second. In general, under nonicing conditions, the configurations with diverging ramp walls maintained, vent-tube pressures greater than the required marginal value of 2 inches of water positive pressure differential between the fuel cell and the compartment containing the fuel cell for a range of angles of attack from 0 to 14deg at a tunnel-air velocity of approximately 240 feet per second. A configuration haying divergIng ramp sldewalls, a 7deg ramp angle; and vent tubes manifold,ed to a common plenum chamber opening through a slot In the ramp floor gave the greatest vent-tube pressures for all the configurations investigated. The use of the plenum chamber resulted in uniform pressures in all vent tubes. In a cloud-icing condition, roughness caused by ice formations on the airfoil surface ahead of the vent ramp, rather than icing of the vent configuration, caused a rapid loss in vent-tube pressures during the first few minutes of an icing period. Only the configuration having diverging ramp sidewalls, a 7 ramp angle, and a common plenum chamber maintained the required vent-tube pressures throughout a 60-minute icing period, although the ice formations on this configuration were more severe than those observed for the other configurations. No complete closure of vent-tube openings occurred for the configurations investigated. A simulated freezing-rain condition caused a greater and more rapid vent-tube pressure loss than was observed for a cloud-icing condition.
    Keywords: AERODYNAMICS
    Type: NACA-TN-1789
    Format: application/pdf
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  • 74
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    Possibilities for drag reduction by boundary layer control (1946)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The mechanics of laminar boundary layer transition are reviewed. Drag possibilities for boundary layer control are analyzed using assumed conditions of transition Reynolds number, inlet loss, number of slots, blower efficiency, and duct losses. Although the results of such analysis are highly favorable, those obtained by experimental investigations yield conflicting results, showing only small gains, and sometimes losses. Reduction of this data indicates that there is a lower limit to the quantity of air which must be removed at the slot in order to stabilize the laminar flow. The removal of insufficient air permits transition to occur while the removal of excessive amounts of air results in high power costs, with a net drag increases. With the estimated value of flow coefficient and duct losses equal to half the dynamic pressure, drag reductions of 50% may be obtained; with twice this flow coefficient, the drag saving is reduced to 25%.
    Keywords: AERODYNAMICS
    Type: NASA-CR-145337 , D-7625
    Format: application/pdf
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  • 75
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    Investigation of suction-slot shapes for controlling a turbulent boundary layer (1947)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Keywords: AERODYNAMICS
    Type: NACA-TN-1292 , NASA-TM-79866
    Format: application/pdf
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  • 76
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    Blade Motion and Bouncing Tests of KD-1 Autogiro (1945)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: There are forwarded herewith the results of blade motion and bouncing tests on the Kellett KD-1 three-bladed autogiro. Motion picture records and two-component accelerometer records were taken in flight during glides at air speeds from 30 miles per hour to 100 miles per hour indicator readings. Calibration curves of correct indicated air speed and rotor speed as functions of air speed meter reading were established with a trailing pitot-static head and a rotoscope, at 2,000 ft. altitude and an air density of 0.00231 slug/ cu. ft., all tests being made at approximately that density.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-MR-X-1935
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  • 77
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    Experimental investigation of the aerodynamic effects of distributed spanwise blowing on a fighter configuration (1948)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The results of wind tunnel tests at NASA Langley targeted at the performance and configurational characteristics of 0.1 and 0.13 scale model spanwise blowing (SWB) jet wing concepts are reported. The concept involves redirection of engine compressor bleed air to provide SWB at the fuselage-wing juncture near the wing leading edge. The tests covered the orientation of the outer panel nozzles, the effects of SWB operation on the performance of leading and trailing edge flaps and the effects of SWB on lateral stability. The trials were run at low speeds and angles of attack from 24-45 deg (landing). Both lift and longitudinal stability improved with the SWB, stall and leading edge vortex breakdown were delayed and performance increased with the SWB rate. Lateral stability was degraded below 20 deg angle of attack while instabilities were delayed above 20 deg due to roll damping.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-2195
    Format: text
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  • 78
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    Performance of the Modified V-1710-93 Engine-Stage Supercharger with a Constant-Area Vaneless Diffuser (1946)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: As part of an investigation to increase the power output of the V-1710-93 engine at altitude, the engine-stage supercharger was combined with a constant-area vaneless diffuser designed to improve the performance of the engine-stage supercharger at the rated engine operating point. The performance of the modified supercharger was investigated in a variable-component supercharger test rig and compared with that of the standard supercharger with an 8-vaned diffuser. A separate evaluation of the component efficiencies and a study of the flow characteristics of the modified supercharger was made possible by internal diffuser instrumentation. At the volume flow required by the engine for rated operating conditions, the modified supercharger increased the over-all adiabatic efficiency 0.05 and the over-all pressure coefficient 0.035. Furthermore, the capacity of the engine-stage supercharger was increased by replacing the standard 8-vaned diffuser with the vaneless diffuser. The peak over-all adiabatic efficiency for the modified supercharger, however, was 0.05 to 0.07 lower than that of the standard unit over the range of tip speeds investigated. The improved performance of the modified supercharger at rated engine operating conditions resulted from a shift of the point of peak adiabatic efficiency and pressure coefficient of the standard supercharger to a higher flow. The energy loss through the vaneless diffuser was found to be small. Because of the restricted diffuser diameter, however, diffusion was inadequate, which resulted in a relatively small static-pressure rise through the diffuser, high diffuser-exit velocities, and excessive collector-case losses.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E6K22
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  • 79
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    On the Sound Field of a Rotating Propeller (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: The sound field of a rotating propeller is teated theoretically on the basis of aerodynamic principles. For the lower harmonics, the directional characteristics and the radiated sound energy are determined and are in conformity with existing experimental results.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1195 , Physikalische Zeitschrit der Sowjetinion: Physical magazine of the Soviet Union volume 9 number 1; 9; 1; 57-71
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  • 80
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    Two-Dimensional Wind-Tunnel Investigation of Modified NACA 65(sub 112)-111 Airfoil with 35-Percent-Chord Slotted Flap to Determine Pitching-Moment Characteristics and Effects of Roughness (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation has been made in the Langley two-dimensional low-turbulence pressure tunnel to develop the optimum configuration of a 0.35-chord slotted flap on an NACA 65(sub 1120)-111 airfoil section modified by removing the trailing-edge cusp. The section pitching-moment characteristics and the effects of standard roughness on the section characteristics were determined for the flap retracted at Reynolds numbers ranging from 3.0 x 10(exp 6) to 9.0 x 10(exp 6).
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L7B18
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  • 81
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    Ditching Tests of a 1/18-Scale Model of the Lockheed Constellation Airplane (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Tests were made of a 1/18-scale dynamically similar model of the Lockheed Constellation airplane to investigate its ditching characteristics and proper ditching technique. Scale-strength bottoms were used to reproduce probable damage to the fuselage. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and fuselage configuration were simulated. The behavior of the model was determined from visual observations, by recording the longitudinal decelerations, and by taking motion pictures of the ditchings. Data are presented in tabular form, sequence photographs, and time-history deceleration curves. It was concluded that the airplane should be ditched at a medium nose-high landing attitude with the landing flaps full down. The airplane will probably make a deep run with heavy spray and may even dive slightly. The fuselage will be damaged and leak substantially but in calm water probably will not flood rapidly. Maximum longitudinal decelerations in a calm-water ditching will be about 4g.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL8K18
    Format: application/pdf
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  • 82
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    Measurements of the Lateral and Directional Stability and Control Characteristics of a P-51H Airplane (AAF No. 44-64164) (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Flight tests of a P-51H airplane with two different vertical-tail assemblies were made to determine lateral and directional stability and control characteristics. The airplane had satisfactory directional stability in the landing, approach, and wave-off conditions with either tail. In the power-on clean and glide conditions, however, the airplane had weak directional stability with the original tail. The production tail, which had a 7-inch fin extension and a shorter span rudder, improved the directional stability in the power-on clean and glide conditions, but the stability was still weak in the power-on clean condition. Increased altitude in either case caused a slight decrease in the stability. The rudder-trim-force change with speed with either vertical-tail assembly was high. The general aileron control characteristics were satisfactory but the aileron effectiveness failed to meet the Army handling-qualities requirements.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL7L11
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  • 83
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    New Method of Determining the Polar Curve of an Airplane in Flight (1945)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A fundamental defect of existing methods for the determination of the polar of an airplane in flight is the impossibility of obtaining the thrust or the resistance of the propeller for any type airplane with any type engine. The new method is based on the premise that for zero propeller thrust the mean angle of attack of the blade is approximately the same for all propellers if this angle is reckoned from the aerodynamic chord of the profile section. This angle was determined from flight tests. Knowing the mean angle of the blade setting the angle of attack of the propeller blade at zero thrust can be found and the propeller speed in gliding obtained. The experimental check of the new method carried out on several airplanes gave positive results. The basic assumptions for the construction of the polars and the method of analyzing the flight data are given.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1076 , Report of the Central Aero-Hydrodynamical Inst.; Rept-418
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  • 84
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    An Investigation of the Aerodynamic Characteristics of an 0.08-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley High-Speed 7-by 10-Foot Tunnel: TED No. DE308 (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An analysis of the estimated high-speed flying qualities of the Chance Vought XF7U-1 airplane in the Mach number range from 0.40 to 0.91 has been made, based on tests of an 0.08-scale model of this airplane in the Langley high-speed 7- by 10-foot wind tunnel. The analysis indicates longitudinal control-position instability at transonic speeds, but the accompanying trim changes are not large. Control-position maneuvering stability, however, is present for all speeds. Longitudinal lateral control appear adequate, but the damping of the short-period longitudinal and lateral oscillations at high altitudes is poor and may require artificial damping.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL8J15-Pt-6
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  • 85
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    Landing Characteristics in Waves of Three Dynamic Models of Flying Boats (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Powered models of three different flying boats were landed in oncoming wave of various heights and lengths. The resulting motions and acceleration were recorded to survey the effects of varying the trim at landing, the deceleration after landing, and the size of the waves. One of the models had an unusually long afterbody. The data for landing with normal rates of deceleration indicated that the most severe motions and accelerations were likely to occur at some period of the landing run subsequent to the initial impact. Landings made at abnormally low trims led to unusually severe bounces during the runout. The least severe landing occurred after a small lending when the model was rapidly decelerated at about 0.4 g in a simulation of the proposed use of braking devices. The severity of the landings increased with wave height and was at a maximum when the wave length was of the order of from one and one-half to twice the over-all length of the model. The models with afterbodies of moderate length frequently bounced clear of the water into a stalled attitude at speeds below flying speed. The model with the long afterbody had less tendency to bounce from the waves and consequently showed less severe accelerations during the landing run than the models with moderate lengths of afterbody.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L6L13
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  • 86
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    Aerodynamic Characteristics of a Number of Modified NACA Four-Digit-Series Airfoil Sections (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Theoretical pressure distributions and measured lift, drag, and pitching moment characteristics at three values of Reynolds number are presented for a group of NACA four-digit-series airfoil sections modified for high-speed applications. The effectiveness of flaps applied to these airfoils and the effect of standard leading-edge roughness were also investigated at one value of Reynolds number. Results are also presented of tests of three conventional NACA four-digit-series airfoil sections.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L7I22
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  • 87
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    Ditching Tests of a 1/9-Size Model of the Army P-38 Airplane in Langley Tank No. 2 and at the Outdoor Catapult (1946)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A dynamically similar model of the Army P-38 airplane was tested to determine the best way to land this airplane on the water and to determine its probable ditching performance. The tests consisted of ditching the model at various landing attitudes, flap settings, speeds, weights, and conditions of simulated damage. The model was ditched in calm water from the tank towing carriage and a few ditching were made in both calm and rough water at the outdoor catapult. The performance of the model was determined by making visual observations, by recording lengths of run and time histories of decelerations, and by taking motion pictures of the ditchings.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L6J17
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  • 88
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    Distribution of Structural Weight of Wing Along the Span (1946)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: In the present report the true weight distribution law of the wing structure along the span is investigated. It is shown that the triangular distribution and that based on the proportionality to the chords do not correspond to the actual weight distribution, On the basis of extensive data on wings of the CAHI type airplane formulas are obtained from which it is possible to determine the true diagram of the structural weight distribution along the span from a knowledge of only the geometrical dimensions of the wing. At the end of the paper data are presented showing how the structural weight is distributed between the straight center portion and the tapered portion as a function of their areas.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1086 , Report of the Central Aero-Hydrodynamical Institute, Moscow; Rept-381
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  • 89
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    Free-Spinning-Tunnel Tests of a 1/29-Scale Model of the Republic XP-91 Airplane with a Vee Tail Installed (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A spin investigation has been conducted in the Langley 20 -foot free-spinning tunnel on a 1/29 - scale model of the Republic XP-91 airplane with vee tail installed. The effects cf control settings and movements upon the effect spin and recovery characteristics of the model were determined for the clean condition (wing tanks removed, landing gear and flaps retracted). The tests were made at a loading simulating that following cruise at altitude and at a time when nearly all fuel was expended. The results indicated that the airplane might not spin at normal spinning-control configuration, but if a spin were obtained, recovery therefrom by full rudder reversal would be satisfactory. It was also indicated that aileron-against settings would lead to violent oscillatory motions and should be avoided.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L7L03
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  • 90
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    Waters Loads on the XJL-1 Hull as Obtained in Langley Impact Basin, TED No. NACA 2413.3 (1946)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation was conducted in the Langley impact basin of the water loads on a half scale model of the XJL-1 hull whose forebody has a vee bottom with exaggerated chine flare. The impact loads, moments, and pressures were determined for a range of landing conditions. A normal full-scale landing speed of 86 miles per hour was represented with effective flight paths ranging from 0.6deg to 11.6deg. Landings were made with both fixed trim and free-to-trim mounting of the float over a trim range of -15deg to 12deg into smooth water and into waves having equivalent full-scale length. of 120 feet and heights ranging from 1 to 4 feet. All data and results presented in this report are given in terms of equivalent full-scale values. Summary tables and illustrative plots are used in presenting the material. The following maximum values of load and pressure are those which are apropos for effective flight paths less than 6.5deg which was the maximum value obtained in tests with the XJL-1 hull model representing full-scale landings with vertical velocity of 4.5 feet per second into 4-foot waves. The maximum local pressure on the flat portion of the bottom is 130 pounds per square inch which was measured on a 2-inch-diameter circular area near the step. The maximum local pressure obtained in the curved area near the chines is 200 pounds per square inch. This pressure was also measured near the step.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L6I03
    Format: application/pdf
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  • 91
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    Longitudinal Stability and Control Characteristics of a B-29 Airplane with a Booster Incorporated in the Elevator Control System to Provide Various Stick-Force and Control-Rate Characteristics (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The longitudinal stability and control characteristics of a B-29 airplane have been measured with a booster incorporated in the elevator control system. Tests were made to determine the effects on the handling qualities of the test airplane of variations in pilots control-force gradients as well as the effects of variations in the maximum rate of control motion supplied by the booster system.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L50D11 , Rept-3130
    Format: application/pdf
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  • 92
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    Free-Spinning-Tunnel Tests of a 1/24-Scale Model of the McDonnell XP-88 Airplane with a Conventional Tail (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation of the spin and recovery characteristics of a 1/24-scale model of the McDonnell XP-88 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The effects of control settings and movements on the erect and inverted spin and recovery characteristics of the model in the normal loading were determined. Tests of the model in the long-range loading also were made. The investigation included tail-modification, spin-recovery parachute, pilot-escape, and rudder-pedal-force tests. Recoveries were generally satisfactory for spins in the normal loading provided the ailerons were not held against the spin. Satisfactory recoveries were obtained regardless of the aileron setting when the leading-edge flaps were deflected and normal recovery technique was used or when the horizontal tail was raised 70 inches, full scale. Recoveries were rapid from all inverted spins obtained. In the long-range loading with tanks on, it may be necessary to jettison the tanks in order to obtain recovery. A 12.0-foot spin-recovery parachute at the tail or a 4.0-foot parachute opened on the outer wing tip (drag coefficient of 0.66) was found to be effective for recoveries from demonstration spins. Test results showed that in an emergency the pilot should attempt to escape from the outboard side of the spinning airplane. The rudder-pedal forces in a spin were indicated to be within the capabilities of the pilot.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L7H21
    Format: application/pdf
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  • 93
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    Flight-Test Evaluation of the Longitudinal Stability and Control Characteristics of 0.5-Scale Models of the Fairchild Lark Pilotless-Aircraft Configuration. Static Longitudinal Stability of Models with Wing Flap Deflections of 0 Deg and 15 Deg, TED No. NACA 2387 (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: From flight tests of 0.5-scale models of the Fairchild Lark pilotless aircraft conducted at the flight test station of the Pilotless Aircraft Research Division at Wallops Island, Va., some evaluations of the static longitudinal stability were obtained by analysis of the short-period oscillations induced by the abrupt movement of the rudder elevators. The analysis shows that for the Lark configuration with wing flap deflections of 0 degrees and 15 degrees the static longitudinal stability decreases slightly up to the critical Mach number and than as the Mach number increases further the stability increases greatly.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L6L17a
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  • 94
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    Evaluation of Gust and Draft Velocities from Flights of P-61C Airplanes within Thunderstorms August 21, 1946 to August 22, 1946 at Orlando, Florida (1946)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Tables I and II of this report summarize the gust and draft velocity data for thunderstorm flights 25 and 26 of August 21, 1946 and August 22, 1946, respectively. These dta were evaluated from records of NACA instruments installed in P-61C airplanes and are of the type presented in reference 1 for previous flights. Table III summarizes the readings of a milliammeter which was used in conjunction with other equipment to indicate ambient air temperature during thunderstorm surveys. These data were read from motion-picture records of the instrument and include all cases in which variations in the instrument indications were noted during the present flights.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L6L02a
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  • 95
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    Force Tests of a 1/5-Scale Model of the McDonnell XP-85 Airplane with Conventional Tail Assembly in the Langley Free-Flight Tunnel (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: At the request of the Air Materiel Command, Army Air Forces an investigation of the low-speed, power-off stability and control characteristics of the McDonnell XP-85 airplane is being conducted in the Langley free-flight tunnel. The XP-85 airplane is a parasite fighter carried in a bomb bay of the B-36 airplane. As a part of the investigation a few force tests were made of a 1/5 scale model of the XP-85 with a conventional tail assembly installed in place of the original design five-unit tail assembly. The total area of the conventional assembly was approximately 80 percent of the area of the five-unit assembly. The results of this investigation showed that the conventional tail assembly gave about the same longitudinal stability characteristics as the original configuration and improved the directional and lateral stability.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L7C26
    Format: application/pdf
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  • 96
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    Flight Tests of a Curtiss No. 838-1C2-18 Three-Blade Propeller Having Trailing-Edge Extensions (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Flight tests to determine propeller performance have been made of a Curtiss No. 838-102-18 three-blade propeller having trailing-edge extensions on a Republic P-47D-28 airplane in climb and high speed. These tests are a part of a general propeller flight-test program at the Langley Laboratory of the National Advisory Committee for Aeronautics. Results of climb tests indicate that when power is changed from approximately 1475 horsepower at 2550 rpm (roughly normal power) to 2400 horsepower at 2700 rpm (approximately military power) there is a loss in propeller efficiency of 3 percent at an altitude of 7000 feet, and 4 percent at 21,000 feet. At an airplane Mach number of 0.7 there is a gain of 9 percent in propeller efficiency when the power coefficient per blade is increased from 0.06 to 0.09. Optimum power coefficient per blade at this Mach number is estimated to be approximately 0.12. An analysis to determine the effect of the addition of extensions on the performance of the basic propeller blades indicates that climb performance was increased but high-speed performance was reduced. Both effects, however, were small.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L7D10
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  • 97
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    Development of Outboard Nacelle for the XB-36 Airplane (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation of two 1/14 scale model configurations of an outboard nacelle for the XB-36 airplane was made in the Langley two-dimensional low-turbulence tunnels over a range of airplane lift coefficients (C (sub L) = 0.409 to C(sub L) = 0.943) for three representative flow conditions. The purpose of the investigation was to develop a low-drag wing-nacelle pusher combination which incorporated an internal air-flow system. The present investigation has led to the development of a nacelle which had external drag coefficients of similar order of magnitude to those obtained previously from tests of an inboard nacelle configuration at the corresponding operating lift coefficients and from approximately one-third to one-half of those of conventional tractor designs having the same ratio of wing thickness to nacelle diameter.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L7G25
    Format: application/pdf
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  • 98
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    An Investigation of the Aerodynamic Characteristics of an 0.08-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley High-Speed 7- by 10-Foot Tunnel. Part II - Basic Lateral Stability Characteristics TED No. NACA DE308 (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Tests have been conducted in the Langley high-speed 7- by 10-foot tunnel over a Mach number range from 0.40 to 0.91 to determine the stability and control characteristics of an 0.08-scale model of the Chance Vought XF7U-1 airplane. The basic lateral stability characteristics of the complete model with undeflected control surfaces are presented in the present report with a very limited analysis of the results.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L7G10-Pt-2
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  • 99
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    Flight Measurements of the Flying Qualities of a Lockheed P-80A Airplane (Army No. 44-85099) - Stalling Characteristics (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: This report contains the flight-test results of the stalling characteristics measured during the flying-qualities investigation of the Lockheed P-8OA airplane (Army No. 44-85099). The tests were conducted in straight and turning flight with and without wing-tip tanks. These tests showed satisfactory stalling characteristics and adequate stall warning for all configurations and conditions tested.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SA7L04
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  • 100
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    Preliminary Results of Nene II Engine Altitude-chamber Performance Investigation (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation is being conducted to determine the altitude performance characteristics of the Nene II engine and its components. The present paper presents the preliminary results obtained using jet nozzle 18.00 inches in diameter, with an area equal to 92.2 percent of the area of the standard jet nozzle for this engine. The experimental results presented are for conditions simulating altitudes from 20,000 to 60,000 feet and ram-pressure ratios from 1.1 to 3.5. These ram-pressure ratios correspond to flight Mach numbers between 0.374 and 1.466. Data obtained with the 18.00 inch-diameter jet nozzle and corrected to standard sea-level conditions showed substantially the same trends with altitude as the data previously obtained with an 18.75-inch-diameter nozzle and with an 18.41-inch-diameter nozzle. Jet thrust, air consumption, and fuel consumption, corrected to standard sea-level conditions, increased rapidly with increasing ram-pressure ratio. In general, corrected net thrust specific fuel consumption increased with increase in ram-pressure ratio. Corrected net thrust decreased with an increase in ram-pressure ratio at an engine speed of 8000 rpm. At corrected engine speeds between 8000 and 10,800 rpm, net thrust first decreased with an increase in ram-pressure ratio and then increased with further increase in ram pressure ratio; at corrected engine speeds above 10,800 rpm, net thrust increased continuously with increase in ram-pressure ratio. Tail-pipe temperature decreased with an increase in ram-pressure ratio.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E8H06
    Format: application/pdf
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