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  • Aerodynamics  (74)
  • Witterung  (31)
  • AERODYNAMICS
  • Animals
  • 1940-1944  (81)
  • 1925-1929
Collection
Years
Year
  • 1
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    In:  Landwirtschaftl. Jahrbuch 64:241-296
    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
    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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    In:  Vereinigten Friedrichs-Universität Halle-Wittenberg, Halle.
    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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  • 4
    Publication Date: 1929
    Description: Ergebnisse (Rangordungs- und Korrelationsmethode) der Beziehung zwischen Witterung und Ertrag vieler Kulturen eingeteilt nach Monaten KATASTER-BESCHREIBUNG: Einfluss der Temperatur und des Niederschlags auf den Ertrag folgender Kulturpflanzen: Winterweizen, Winterroggen, Dinkel, Sommerweizen, Sommerroggen, Sommergerste, Hafer, Hopfen, Luzerne, Rotklee, Wiesen, Kartoffeln) KATASTER-DETAIL: Delta T (Vegetationszeit) -, dann Ertrag (Winter- und Sommergetreide) +; Delta T (Winter, Juni und Juli) -, dann Ertrag (Sommergetreide) +; Delta Nied (Winter) +, dann Ertrag (Getreide) -; Delta T (September) - und Delta Nied (Vegetationszeit) +, dann Ertrag (Futterpflanzen) +; Details für einzelne Kulturpflanzen: siehe Artikel
    Keywords: Württemberg ; 1899-1913 ; Ertrag ; Hafer ; Korrelationsmethode ; Niederschlag ; Rangordnungsmethode ; Temperatur ; Weizen ; Witterung
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  • 5
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    In:  Ztschr. angew. Ent. 29: 412-441 u. 601-635
    Publication Date: 1942
    Description: Beschreibung der Biologie der Buschhornblattwespe vom Schlüpfen, über die Entwicklung bis hin zum Überliegen und die abiotischen Sterlichkeitsursachen, u.a. witterungsbedingt KATASTER-BESCHREIBUNG: Beginn der Frühjahrsgeneration ist klima- und wetterbedingt, unter günstigen Bedingungen (milder Winter) bereits im Januar Beginn der Entwicklung und Schlupfbeginn ab Anfang April KATASTER-DETAIL: Tmit- (Spätfrühjahr und Frühwinterwitterung) , dann Schlupfbeginn später und Anteil der Überlieger höher
    Keywords: Mecklenburg-Vorpommern ; 1937-1940 ; Insekten ; Kiefer ; Pflanzenschädling ; Temperatur ; Vegetationsperiode ; Wachstum ; Witterung
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  • 6
    Publication Date: 1929
    Description: Einfluss der Witterung ist Gattungs- teils sortenabhängig, und wechselt mit der Lage der Orte. Trockenheit im Vorjahr begünstigt die Ernteerträge, KATASTER-BESCHREIBUNG: Trockenheit im Vorjahr begünstigt verbunden mit hoher Temperatur, geringer Luftfeuchtigkeit und langer Sönnenscheindauer, mit niedriger Temperatur, hoher Luftfeuchte, kurzer Sonnenscheindauer im Erntejahr, wirkt positiv auf die Ernteerträge für bestimmte Apfel - und Birnensorten, umgekehrte Beziehung insbesondere bei Früh-, Herbst- und Winterbirnensorten KATASTER-DETAIL:
    Keywords: Niedersachsen ; 1900-1923 ; Apfel ; Ertrag ; Trockenheit ; Witterung ; Obst ; Birne
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  • 7
    Publication Date: 1929
    Description: vgl. Neustädt KATASTER-BESCHREIBUNG: Zusammenhang Witterungsfaktoren in wachstumsrelevanten Zeitspannen mit dem Ertrag verschiedener Kulturen 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) ++; (Informationen zu den weiteren landwirtschaftlicher Kulturpflanzen: siehe Artikel)
    Keywords: Mitteldeutschland ; 1900-1926 ; Kartoffeln ; Ertrag ; Niederschlag ; Roggen ; Temperatur ; Witterung ; Hackfrüchte
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  • 8
    Publication Date: 1929
    Description: Einfluß der Witterung auf die Qualität von Weizen KATASTER-BESCHREIBUNG: Witterungsverhältnisse der letzten 5 bis höchstens 10 Tage vor der Gelbreife sind von entscheidendem Einfluss, Backqualität nimmt von kontinentalem zum maritimen Klima ab KATASTER-DETAIL: Tmit+, Sonn+, Nied-, dann gute Qualität Nied+, dann Tausendkorngewicht + aber Nied**, dann Tausendkorngewicht - und N-Gehalt +
    Keywords: Mitteldeutschland ; 1900-1925 ; Ertrag ; Korrelationsmethode ; Landwirtschaft ; Niederschlag ; Temperatur ; Trockenheit ; Weizen ; Witterung ; Sonnenscheindauer
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  • 9
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    In:  Kühn-Archiv, Berlin, Band XX, Seite 223-301
    Publication Date: 1928
    Description: Auswertung von 27 Versuchsjahren, Bestimmung einer kritischen Periode für die Mindestniederschlagshöhe durch Auswertung der Klimaparmeter in einzelnen Bezirken mittels Rangkorrelationskoeffizienten KATASTER-BESCHREIBUNG: Zusammenhang zwischen der Niederschlagshöhe und dem Ertrag von Zuckerrüben, Zusammenhang zwischen der Sonnenscheindauer und dem Zuckergehalt von Zuckerrüben KATASTER-DETAIL: Delta Nied+: Nied 〉 175 mm (Juli-September), dann Ertragssteigerung bei ZR; Delta Sonn +: Sonn〉 4.43 h (September -Oktober), dann hohe Zuckergehalte bei ZR
    Keywords: Sachsen-Anhalt ; 1900-1926 ; Zuckerrüben ; Niederschlag ; Rangordnungsmethode ; Temperatur ; Witterung
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  • 10
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    In:  Landwirtschaftl. Jahrbuch 68:642-686
    Publication Date: 1942
    Description: Ableitung kritischer Faktoren (Temperaturoptima und Wasserversorgung) in einzelnen Wachstumsstadien KATASTER-BESCHREIBUNG: Zusammenhang zwischen Temperaturänderung während der Blüte von Weizen und dem Ertrag KATASTER-DETAIL: Delta T + und -: Tmit von 14-15°C, Änderung um +1 K auf 16°C, aber auch Rückgang um 2K auf 13°C, dann Rückgang des Ertrages
    Keywords: Kölner Bucht ; 1907-37 ; Boden ; Ertrag ; Korrelationsmethode ; Niederschlag ; Roggen ; Temperatur ; Weizen ; Witterung ; Düngung ; Hackfrüchte
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  • 11
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    In:  Landw. Jahrbuch 68:537-558
    Publication Date: 1929
    Description: Untersuchungen der Beziehungen zwischen Pferdebohne (Vicia faba L.) und der Witterung. Einteilung des Wachstums in Abschnitte KATASTER-BESCHREIBUNG: Einfluss der Witterung auf die Entwicklung und den Ertrag der Pferdebohne KATASTER-DETAIL: Delta T + und Delta Sonn +, dann Reife + (früher); Delta T +, dann 1. Wachstumsabschnitt (vom Auflaufen bis zum Blütebeginnn) - (kürzer); Delta T + und Delta Sonn +, dann 3. Wachstumsabschnitt (Reifezeit) - (kürzer); Delta T +, dann Gesamtwachstumszeit +; Delta Nied +, dann Gesamtwachstumszeit -; Delta T (Gesamtwachstumszeit,Jugendzeit) +, dann Kornzahl +; Delta Sonn (Blütezeit) +, dann Kornzahl +; Delta Nied +, dann Kornzahl -; Delta T (Reifezeit) - und Delta Nied (Reifezeit) +, dann Pilzbefall + und somit Kornzahl -; Delta T +, dann Kornschwere -; Delta Nied (10 Tage vor bis 10 Tage nach Blütenende) +, dann Kornschwere +; Delta T +, dann Hülsenzahl +; Delta Nied +, dann Hülsenzahl -; Delta Nied (alle Wachstumszeiten) + und Delta T (bis zum Blütenende) + und Delta Sonn -, dann Strohgewicht +;
    Keywords: Freising, Bayern ; 1921-1926 ; Ertrag ; Witterung ; Gemüse
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  • 12
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    In:  Deut. Landwirtschaflt. Presse 55:94-95.
    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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  • 13
    Publication Date: 1929
    Description: Einfluss der Witterungsfaktoren auf verschiedene Kulturen und die Betriebssysteme KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland ; Witterung
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  • 14
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    In:  Zeitschrift für Pflanzenernährung, Düngung, Bodenkunde 6:490-496.
    Publication Date: 1927
    Description: Einfluss der Witterungsfaktoren Niederschlag, Temperatur und Sonnenscheindauer auf die Erträge KATASTER-BESCHREIBUNG: Einteilung der Temperatur in Klassen (stark, mittel, gering) und die Beurteilung auf die Erträge in den 6 Provinzen des deutschen Reiches, mit Vermehrung der Niederschlage wahrend der Vegetationszeit Zunahme der Halmfrüchte und der Kartoffeln im gröBten Teile des PreuBischen Staates anfangs, jedoch nd spater wieder abnehmender Trend KATASTER-DETAIL: Delta T+ (April-Augut), dann Winterweizenerträge + in OstpreuBen, Brandenburg und Sachsen Delte T++ (April-August), dann Winterweizenerträge ++ in Ostpreußen, aber - in Brandenburg und Sachsen Delta T- (April-Augut), dann Winterweizenerträge - in Hannover und der Rheinprovinz Delta T+ (+0.1° Erhöhung Temperaturmittel der Monate April bis September), dann Kartoffel+ in OstpreuBen und Schlesien
    Keywords: Deutschland, teilw. einzelne Regionen ; 1899-1913 ; Ertrag ; Niederschlag ; Temperatur ; Witterung ; Sonnenscheindauer
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  • 15
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    In:  Die Kartoffel, S. 66
    Publication Date: 1926
    Description: Zusammenhang zwischen der Witterung und der Stärkeeinlagerung bei Kartoffeln KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Kartoffeln ; Ertrag ; Witterung
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  • 16
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    In:  Mitt. DLG, S. 128
    Publication Date: 1928
    Description: Zusammenhang zwischen der Witterung und den Knollenerträgen KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Kartoffeln ; Ertrag ; Witterung
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  • 17
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    In:  Zeitschr. Pflanzenbau 2.
    Publication Date: 1925
    Description: Zusammenhang Witterung und Knollenansatz und -gewicht bei Kartoffeln KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Kartoffeln ; Ertrag ; Witterung
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  • 18
    Publication Date: 1942
    Description: Betrachtung des Klimas (Temperatur und Niederschlag) in Dekaden und Bildung von Ertrags-, Temperatur- und Niederschlagsklassen und daraus Ableitungen über die Beziehungen Ertrag und Witterung KATASTER-BESCHREIBUNG: Einfluss der Witterung (Temperatur, Niederschlag) auf den Ertrag KATASTER-DETAIL: Delta T (März) + und Delta Nied (März) +, dann Erträge +; Delta T (April -, dann Erträge +; Delta Nied (Ende Juni,Ende Juli)-, dann Erträge + Delta T (Anfang Juli) +, dann Erträge +
    Keywords: Schlesien ; 1926-38 ; Boden ; Ertrag ; Niederschlag ; Weizen ; Witterung
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  • 19
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    In:  Kühn-Archiv 20:140-222.
    Publication Date: 1929
    Description: Untersuchungen an Ernteergebnissen mittels Rangordnungs- und Korrelationsmethode zur Abhängigkeit von den Witterungsfaktoren. Untersucht wurden die Erträge von Weizen, Roggen, Sommergerste, Hafer, Erbsen und Zuckerrüben KATASTER-BESCHREIBUNG: Einfluss der Witterung (Temperatur, Niederschlag, Sonnenscheindauer) auf die Erträge der Kurlturpflanzen KATASTER-DETAIL: Delta T (Oktober, November) - und Delta T (Januar, Februar) +, dann Erträge (Weizen) +; Delta Nied (April, Mai) + und Delta Nied (Februar, März) -, dann Erträge (Weizen) +; Delta Sonn (März) +, dann Erträge (Weizen) +; Delta Nied (Mai - Zeit des Schossens) +, dann Erträge (Roggen) +; Delta T (November) -, dann Erträge (Roggen) +; Delta Nied (April, Juni) + und Delta T (April, Juni) -, dann Erträge (Sommergerste) +; Nied (April, Juni) 〉 180mm, dann Erträge (Sommergerste) -; Delta Sonn (März, April) + und Delta Sonn (Mai) -, dann Erträge (Sommergerste) +; Delta Nied (April bis Juni) +, dann Erträge (Hafer) +; Delta Sonn (März, April) +, dann Erträge (Hafer) +; Delta T (Juni) -, dann Erträge (Hafer) +; Delta Nied (Juni, September) +, dann Erträge (Zuckerrübe) +; Delta Nied (August) +, Zuckergehalt +; Delta T (Juni) +, dann Erträge (Zuckerrübe) +; Delta Sonn (September) +, Qualität der Ernte +; Delta Sonn (März, April) + und Delta Sonn (Mai, Juni) -, dann Erträge (Getreide) +;
    Keywords: Mansfelder See- und Saalkreis, Kreis Querfurt, Kreis Merseburg ; 1900-1925 ; Zuckerrüben ; Hafer ; Niederschlag ; Roggen ; Temperatur ; Weizen ; Witterung ; Sonnenscheindauer ; Gerste ; Erbsen
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  • 20
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    In:  Der Kartoffelbau, Nr. 69
    Publication Date: 1925
    Description: Zusammenhang der Witterungselemente, insbesondere der Sommerniederschläge zum Ertrag bei Kartoffeln KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Breslau ; 1901-1921 ; Kartoffeln ; Ertrag ; Witterung
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  • 21
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    In:  Kühn-Archiv:53-78.
    Publication Date: 1925
    Description: Einführung der Rangordnungs- und Korrelationsmethode anhand langjähriger Beobachtungen, Einfluss des Niederschlages und der Temperatur auf den Ertrag von Erbsen, Kartoffeln, Weizen, Hafer und Roggen KATASTER-BESCHREIBUNG: Einfluss der Witterung (Temperatur und Niederschlag) auf den Ertrag KATASTER-DETAIL: Delta T (März und April) + und Delta Nied (März und April) -, dann Erträge (Erbsen) +; Delta T (Mai und Juni) - und Delta Nied (Mai und Juni) +, dann Erträge (Erbse) +; Delta T (Oktober Vorjahr) +, dann Erträge (Kartoffel) +; Delta T (März) + und Delta T (Mai und Juni) -, dann Erträge (Winterweizen) +; Delta Nied (Januar bis März)-, dann Erträge (Hafer) +; Delta Nied (Januar bis März)-, dann Erträge (Winterroggen) +;
    Keywords: Halle ; 1893-25 ; Kartoffeln ; Ertrag ; Fichte ; Hafer ; Korrelationsmethode ; Niederschlag ; Rangordnungsmethode ; Roggen ; Temperatur ; Weizen ; Witterung
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  • 22
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    In:  Diss., Göttingen
    Publication Date: 1925
    Description: Ergebnisse ( Korrelationsmethode) der Bezeihung zwischen Witterung und Ertrag vieler Kulturen eingeteilt nach Monaten KATASTER-BESCHREIBUNG: Beziehungen zwischen Witterung (Temperatur und Niederschlag)und Ernte KATASTER-DETAIL: Delta Nied (erste 10 Blütetage) -, dann Ertrag (Roggen) +; Delta Nied (Beginn der Blüte bis 10 tage nach Ende der Blüte)-, dann Ertrag (Winterweizen) +; Delta Nied (während der 20 Tage nach Beginn der Blüte) -, dann Ertrag (Sommerweizen) +; Delta Tmit (während der 20 Tage nach dem Aufgang) -, dann Ertrag (Hafer) +; Delta Tmin (während der 20 Tage nach dem Aufgang) -, dann Ertrag (Gerste) +; Delta Tmit (während der 20 Tage nach Beginn der Blüte) -, dann Ertrag (Kartoffeln) +; Delta Nied (vom Aufgang bis zum Beginn der Blüte) -, dann Ertrag (Erbsen) +; Delta Nied +, dann Ertrag (Vietsbohnen) +;
    Keywords: Göttingen ; 1901-1922 ; Kartoffeln ; Ertrag ; Hafer ; Korrelationsmethode ; Niederschlag ; Temperatur ; Weizen ; Witterung ; Erbsen
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  • 23
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    In:  Landw. Wochenschrift für die Provinz Sachsen und Anhalt, Hallle 18:428ff.
    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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  • 24
    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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  • 25
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    In:  Zeitschrift für Pflanzenernährung, Düngung, Bodenkunde 16.
    Publication Date: 1926
    Description: Beziehungen zwischen Witterung und Ernteertrag KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Hohenheim (Baden-Württemberg) ; 1914-25 ; Ertrag ; Witterung
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  • 26
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    In:  Landw. Jahrbuch Berlin 63(1):1-81
    Publication Date: 1926
    Description: Auszug aus der Diss. KATASTER-BESCHREIBUNG: Beziehungen zwischen Witterung (Temperatur und Niederschlag)und Ernte KATASTER-DETAIL:
    Keywords: Göttingen ; 1901-1922 ; Ertrag ; Korrelationsmethode ; Niederschlag ; Temperatur ; Witterung ; Hackfrüchte ; Erbsen
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  • 27
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    In:  Klima / Boden / Ernte Verlag C.V. Engelhard, Berlin. p. 7, 114-127
    Publication Date: 1942
    Description: Beziehung zwischen Witterungsablauf und Bodenzustand und deren Auswirkung auf Pflanzenwuchs und Ernte KATASTER-BESCHREIBUNG: Einfluss der Witterung auf den Ertrag von Kartoffeln KATASTER-DETAIL: Delta T (April bis Juli) -, dann Erträge (Kartoffel) +; Delta Nied (April bis Juli) -, dann Erträge (Kartoffel) -
    Keywords: Gesamtpreußen, Deutschland,Schlesien ; 1921-1932,1934 ; Zuckerrüben ; Kartoffeln ; Ertrag ; Hafer ; Landwirtschaft ; Niederschlag ; Temperatur ; Witterung ; Hackfrüchte
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  • 28
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    In:  Zeitschrift für Acker- und Pflanzenbau 3:330-334.
    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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    In:  Intern. Agrik.-Wiss. Rundsch. N.F. 1;p.406-424
    Publication Date: 1925
    Description: Der Autor fasst in einer Literaturstudie Forschungsergebnisse und -erkenntnisse von Studien zum Zusammenhang zwischen klimatischen Parametern und dem Auftreten verschiedener Pflanzenkrankheiten aus Feldversuchen zusammen und vergleicht diese mit eigenen Beobachtungen aus Indien. Aus dem Literaturstudium gewonnene Kardinalwerte für verschiedene Pflanzenkrankheiten sind enthalten. Schwerpunkte der Sammlung an Erkenntnissen stellen Indien und die USA dar. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Indien, USA, Welt ; 1900-1925 ; Pflanzenkrankheit ; Witterung
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  • 30
    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
    facet.materialart.
    Unknown
    In:  Georgine, Jahrgang 102, Nr. 68, p. 806-807
    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
    facet.materialart.
    Unknown
    In:  CASI
    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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  • 33
    Publication Date: 2018-06-05
    Description: As part of the program of flight tests of airplane propellers to determine compressibility effects at high speeds, preliminary flights have been made with a conventional three-blade propeller (Hamilton Standard 3155-6) on a Bell YP-39 airplane. This preliminary report presents the high-speed data obtained thus far with a brief analysis of the results.
    Keywords: Aerodynamics
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  • 34
    Publication Date: 2019-06-28
    Description: Problems involved in the stability and control of tailless airplanes are discussed. Such factors as the location of the aerodynamic center and its effect on the longitudinal stability, longitudinal trim with high-lift devices, the effects of various changes in the shape of the wing on lateral stability, and the effects of nacelles are covered. It appears that sufficient stability and controllability can be secured without sweepback. With sweepback, a flap over the center section of the wing may be used to serve the dual purpose of elevator control and high-lift device. Sweepback introduces undesirable stalling characteristics, however, and may require auxiliary devices to prevent stalling of the tips.
    Keywords: Aerodynamics
    Type: NACA-TN-837
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  • 35
    Publication Date: 2019-06-28
    Description: An investigation was made of the flow downstream from a "two-dimensional" grid formed of parallel rods. In both two and three dimensional jet fields there is a critical range of grid density below which the downstream flow is stable and above which it is unstable. The flow can be completely stabilized by means of an adequate lateral contraction beginning immediately after the grid or by use of a fine-mesh damping screen parallel to the grid plane and within a definite range of positions downstream from the grid.
    Keywords: Aerodynamics
    Type: NACA-WR-W-90 , NACA-ACR-4H24
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  • 36
    Publication Date: 2019-06-28
    Description: Problem of improving thrust at low speeds is primarily one of reducing angle of attack of operation of sections to improve L/D or reducing blade helix angle. An analysis, based on recent propeller data, is presented for determining improvements in thrust or efficiency which could be obtained by increased number of blades, increased blade width, increased diameter, dual rotation, and two-speed gearing. All methods were found very effective, particularly two-speed gearing.
    Keywords: Aerodynamics
    Type: NACA-WR-L-483
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  • 37
    Publication Date: 2019-06-28
    Description: Test of a ducted body with Internal flow were made in the 8-foot high-speed wind tunnel for the purpose of studying the effects on external drag and an critical speed of the addition of efficient inlet and outlet openings to a basic streamline shape. Drag tests of a 13.6- inch-diameter streamline body of fineness ratio 6.14 were made at Mach numbers ranging from 0.20 to 0.75. The model was centrally mounted on a 9-percent-thick airfoil and was designed to have an efficient airfoil-body juncture and a high critical speed. An air inlet at the nose and various outlets at the tail were added: drag and internal-flow data were obtained over the given speed range. The critical speed of the ducted bodies was found to be as high as that of the streamline body. The external - drag with air flow through the body did not exceed the drag of the basic streamline shape. No appreciable variation in the efficiency of the diffuser section of the internal duct occurred throughout the Mach number range of the tests.
    Keywords: Aerodynamics
    Type: NACA-WR-L-486
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  • 38
    Publication Date: 2019-06-28
    Description: Data taken from tests at constant speed to establish trim limits of stability, tests at accelerated speeds to determine stable limits of center of gravity shift, and tests at decelerated speeds to obtain landing characteristics of several model hull forms were used to establish hull design effect on longitudinal stability of porpoising. Results show a reduction of dead rise angle as being the only investigated factor reducing low trim limit. Various methods of reducing afterbody interference increased upper trim limit
    Keywords: Aerodynamics
    Type: NACA-WR-L-468
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  • 39
    Publication Date: 2019-06-28
    Description: In order to determine the critical stresses caused by an outward acting pressure on the upper surface of a wing due to the difference in internal and external pressures, torsional tests were made on two curved-sheet specimens subjected to an outward acting normal pressure. Results show that an outward acting normal pressure appreciable raises the critical shear stress for an unstiffened curved sheet; the absolute increase in critical shear stress is slightly greater for a 30 in. rib spacing than for a 10 in. rib spacing.
    Keywords: Aerodynamics
    Type: NACA-WR-L-416
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  • 40
    Publication Date: 2019-06-28
    Description: Two airfoil plans were used for propeller blades. One is modified Clark Y section designed for structural reliability and the second an NACA 16 airfoil section designed to produce minimum aerodynamic losses. At low air speeds, the propeller designed for aerodynamic effects showed a gain of from 1.5 to 4.0 percent in propulsive efficiency over the conventional type depending on the pitch. Because of the numerous variables involved, the effect of each one on the aerodynamic characteristics of the propellers could not be isolated.
    Keywords: Aerodynamics
    Type: NACA-WR-L-404
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  • 41
    Publication Date: 2019-06-28
    Description: Description is given of flight tests conducted on gun fairings, designed to correct the detrimental effects of the projecting and submerged wing guns on an F4F-3 fighter. It was found that the installation of unfaired guns on a clean wing resulted in a premature stall that increased the stalling speed in the carrier-approach and landing conditions of flight by suitably fairing the guns, it was possible to reduce the stalling speeds to values approaching very nearly the clean-wing values.
    Keywords: Aerodynamics
    Type: NACA-WR-L-247
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  • 42
    Publication Date: 2019-06-28
    Description: Porpoising characteristics were observed on V-body fitted with tail surfaces for different combinations of load, speed, moment of inertia, location of pivot, elevator setting, and tail area. A critical trim was found which was unaltered by elevator setting or tail area. Critical trim was lowered by moving pivot either forward or down or increasing radius or gyration. Increase in mass and moment of inertia increased amplitude of oscillations. Complete results are tabulated and shown graphically.
    Keywords: Aerodynamics
    Type: NACA-WR-L-479
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  • 43
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aerodynamics
    Type: NACA-WR-L-702
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  • 44
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aerodynamics
    Type: NACA-WR-L-493
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  • 45
    Publication Date: 2019-06-28
    Description: Pressure distribution measurements were made over an airfoil with slotted Frise aileron up to 0.76 Mach at various angles of attack and aileron defections. Section characteristics were determined from these pressure data. Results indicated loss of aileron rolling power for deflections ranging from -12 Degrees to -19 Degrees. High stick forces for non-differential deflections incurred at high speed, which were due to overbalancing tendency of up-moving aileron, may precipitate serious control difficulties. Detailed results are presented graphically.
    Keywords: Aerodynamics
    Type: NACA-WR-L-266 , NACA-ACR-L4G12
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  • 46
    Publication Date: 2019-06-28
    Description: Methods are given of determining the potential flow plast an arbitrary cascade of airfoils and the inverse problem of determining an airfoil having a prescribed velocity distribution in cascade. Results indicated that Cartesian mapping function method may be satisfactorily extended to include cascades. Numerical calculation for computing cascades by Cartesian mapping function method is considerably greater than for single airfoils but much less than hitherto required for cascades. Detailed results are presented graphically.
    Keywords: Aerodynamics
    Type: NACA-WR-L-81 , NACA-ARR-L4K22B
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  • 47
    Publication Date: 2019-06-28
    Description: Flight tests were conducted on the OS2U-2 seaplane with simple circular-arc-type ailerons directly connected to the actuating torque tube. Two aileron test installations were made, differing only in the inclination of the projecting surface with the wing's upper surface. The lateral-control characteristics of the airplane were determined from data obtained in stalls and rudder-fixed aileron rolls. The revised ailerons were deficient in maximum rolling effectiveness, but were capable of controlling the rolling tendencies of the airplane near the stall.
    Keywords: Aerodynamics
    Type: NACA-WR-A-32
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  • 48
    Publication Date: 2019-06-28
    Description: This report contains those results of the theory of wings and of wing sections which are of immediate practical value. They are proved and demonstrated by the use of the simple conceptions of "kinetic energy" and "momentum" only, familiar to every engineer; and not by introducing "isogonal transformations" and "vortices," which latter mathematical methods are not essential to the theory and better are used only in papers intended for mathematicians and special experts.
    Keywords: Aerodynamics
    Type: NACA-TR-191
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  • 49
    Publication Date: 2019-06-28
    Description: The pitching and the yawing moments of a vee-type and a conventional type of tail surface were measured. The tests were made in the presence of a fuselage and a wing-fuselage combination in such a way as to determine the moments contributed by the tail surfaces. The results showed that the vee-type tail tested, with a dihedral angle of 35.3 deg, was about 71 percent as effective in pitch as the conventional tail and had a yawing-moment to pitching-moment ratio of 0.3. The conventional tail, the panels of which were all congruent to those of the vee-type tail, had a yawing-moment to pitching-moment ratio of 0.48. These ratios are in fair agreement with values calculated by methods shown in this and previous reports. The values of the measured moments were reduced from 15 to 25 percent of the calculated value by fuselage interference.
    Keywords: Aerodynamics
    Type: NACA-TN-815
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  • 50
    Publication Date: 2019-06-28
    Description: Tests were made in 8-ft high-speed wind tunnel to determine the drag reduction possible by eliminating the barrel jacket of a protruding 50-caliber aircraft gun. It was found that the drag of a standard aircraft gun protruding into the air stream at right angles to the flow can be reduced by 23% by discarding the barrel jacket. At 300 mph and sea-level conditions, this amounts to a decrease in drag of from 83 to 64 pounds. A rough surface finish on the barrel was found to have no adverse effects on the drag of the barrel, the drag being actually less at high Mach Numbers.
    Keywords: Aerodynamics
    Type: NACA-WR-L-581
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  • 51
    Publication Date: 2019-06-28
    Description: Tank tests were made of a hull model of the Hughes-Kaiser cargo airplane for estimates of take-off performance and maximum gross load for take-off. At hump speeds, with the model free to trim, the trim and resistance were high, which resulted in a load-resistance ratio of approximately 4.0 for a gross load coefficient of 0.75. With a 4000,000-lb load, the full size craft may take off in 69 sec over a distance of 5600 ft.
    Keywords: Aerodynamics
    Type: NACA-WR-L-683
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  • 52
    Publication Date: 2019-06-28
    Description: Tests were conducted on hydrofoil assemblies approximating an arrangement for use under seaplanes or surface boats. A series of hydrofoils, each supported by two struts, was towed at various depths ranging from partial submersions to a depth of 5-chord lengths. At depths greater than 4 or 5 chords, the influence of the surface of the water is small; hydrofoils operating at low speed will have characteristics similar to those of airfoils of the same section.
    Keywords: Aerodynamics
    Type: NACA-WR-L-758
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  • 53
    Publication Date: 2019-06-28
    Description: Several tail modifications of the Brewster XSBA-1 scout-bomber were investigated and results compared. Modifications consisted of variation of the chord of the elevator and rudder while the total area of the surfaces is kept constant and variations of the total area of the vertical tail surface. Configuration number 2 reduced trim changes by 50 percent and reduced average elevator control force gradient from 30 to 27 pounds/g. Stick travel required to stall in maneuver was 4.6 inches.
    Keywords: Aerodynamics
    Type: NACA-WR-L-598
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  • 54
    facet.materialart.
    Unknown
    In:  CASI
    Publication Date: 2019-06-28
    Description: Analysis was made to determine characteristics required of a balancing-tab system for ailerons in order to reduce aileron stick forces to any desired magnitude. Series of calculations based on section data were made to determine balancing-tab systems of various chord tabs and ailerons that will give, for a particular airplane, zero rate of aileron hinge moment with aileron deflection and yet will produce same maximum rate of roll as a plain unbalanced 15-percent chord aileron of same span. Effects of rolling velocity and of forces in tab link on aileron hinge moments have been included.
    Keywords: Aerodynamics
    Type: NACA-WR-L-346
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  • 55
    Publication Date: 2019-06-28
    Description: Results of flight tests indicate that profile-drag coefficients which were obtained with the low-drag airfoils were lower than with the conventional types over the range of light coefficients tested. For comparable conditions of the lift coefficient and Reynolds Number, the low-drag airfoils have profile-drag coefficients which may be 27 percent lower than the profile drag of the conventional airfoils tested. Detailed results are presented graphically.
    Keywords: Aerodynamics
    Type: NACA-WR-L-139 , NACA-ACR-L4E31
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  • 56
    facet.materialart.
    Unknown
    In:  CASI
    Publication Date: 2019-06-28
    Description: This report gives the pressure distribution and resistance found by theory and experiment for simple quadrics fixed in an infinite uniform stream of practically incompressible fluid. The experimental values pertain to air and some liquids, especially water; the theoretical refer sometimes to perfect, again to viscid fluids. For the cases treated the concordance of theory and measurement is so close as to make a resume of results desirable. Incidentally formulas for the velocity at all points of the flow field are given, some being new forms for ready use derived in a previous paper. (author)
    Keywords: Aerodynamics
    Type: NACA-TR-253
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  • 57
    Publication Date: 2019-06-28
    Description: Rough conventional, smooth conventional, and laminar-flow or low-drag sections were tested. The items covered are rotor thrust for fixed power in hovering, range and endurance at cruising speed, and power required at high-forward speed. Calculations indicated that a smooth conventional section gives marked performance gains. Smaller gains are obtainable by using a low-drag section. At high speeds or loads the low-drag section is inferior to the smooth conventional section.
    Keywords: Aerodynamics
    Type: NACA-WR-L-26 , NACA-ACR-L4H05
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  • 58
    Publication Date: 2019-06-28
    Description: Tests of 10-ft. diameter, eight-blade, single - and dual - rotating propellers were conducted in 20-ft propeller research tunnel. Propellers were mounted at front end of a streamline body in spinners that covered hubs and parts of shanks. Effect of a symmetrical wing mounted in slipstream was investigated. Blade-angle settings ranged from 20 Degrees to 65 Degrees. Results indicated that dual rotation resulted in gains of from 1 to 8 percent in efficiency over single rotation for eight-blade propellers, but presence of a wing reduced gain about one-half. Greater power absorption caused by dual rotation over flight range and higher efficiency or thrust for range of take-off and climb was indicated
    Keywords: Aerodynamics
    Type: NACA-WR-L-384
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  • 59
    Publication Date: 2019-06-28
    Description: An investigation was made of the cooling characteristics of a P and W R-2800 engine with NACA short-nose high inlet-velocity cowling. The internal aerodynamics of the cowling were studied for ranges of propeller-advance ratio and inlet-velocity ratio obtained by deflection of cowling flaps. Tests included variations of engine power, fuel/air ratio and cooling-air pressure drop. Engine cooling data are presented in the form of cooling correlation curves, and an example for calculation of cooling requirements in flight is included.
    Keywords: Aerodynamics
    Type: NACA-WR-L-207 , NACA-ACR-L4F06
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  • 60
    Publication Date: 2019-06-28
    Description: Investigations were undertaken to improve the ailerons of a P-51 fighter so as to obtain greater effectiveness without increasing the stick forces. Modifications consisted of increasing the deflection range of the aileron to 70 percent and changing the original concave section to a thick section with beveled trailing edge. Results of the modified ailerons showed an increase in effectiveness over the original aileron of 70 percent at low speed and 55 percent at high speeds.
    Keywords: Aerodynamics
    Type: NACA-WR-L-636
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  • 61
    Publication Date: 2019-06-28
    Description: Hinge-moment, lift, and pressure-distribution measurements were made in the two-dimensional test section of the NACA stability tunnel on a blunt-nose balance-type aileron on an NACA 66,2-216 airfoil at speeds up to 360 miles per hour corresponding to a Mach number of 0.475. The tests were made primarily to determine the effect of speed on the action of this type of aileron. The balance-nose radii of the aileron were varied from 0 to 0.02 of the airfoil chord and the gap width was varied from 0.0005 to 0.0107 of the airfoil chord. Tests were also made with the gap sealed.
    Keywords: Aerodynamics
    Type: NACA-WR-L-431 , NACA-ACR-3F11
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  • 62
    Publication Date: 2019-06-28
    Description: Aerodynamics data are obtained for the design of linked balancing tabs and effect of varied tab span and location to produce suitable lateral control characteristics with reasonable stick pressures for high-speed aircraft. Simple and spring-linked balancing tabs may considerably reduce control pressures if aileron system is designed for low maximum aileron deflection. Spring-linked tabs also decrease variation of stick pressure with speed and impart better controlllability at low speeds.
    Keywords: Aerodynamics
    Type: NACA-WR-L-470
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  • 63
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aerodynamics
    Type: NACA-WR-L-318 , NACA-ARR-4A26
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  • 64
    Publication Date: 2019-06-28
    Description: Tests were made of an 0.309-chord double-slotted flap on an NACA 65, 3-118, a equals 1.0 airfoil section to determine drag, lift, and pitching-moment characteristics for a range of flap deflections. Results indicate that combination of a low-drag airfoil and a double-slotted flap, of which the two parts moved as a single unit, gave higher maximum lift coefficients than have been obtained with plain, split, or slotted flaps on low-drag airfoils. Pitching moments were comparable to those obtained with other high-lift devices on conventional airfoils for similar lift coefficients.
    Keywords: Aerodynamics
    Type: NACA-WR-L-697 , NACA-ACR-3I20
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  • 65
    Publication Date: 2019-06-28
    Description: Results are presented for tests of two wings, an NACA 230-series wing and a highly-cambered NACA 66-series wing on a twin-engine pursuit airplane. Auxiliary control flaps were tested in combinations with each wing. Data showing comparison of high-speed aerodynamic characteristics of the model when equipped with each wing, the effect of the auxiliary control flaps on aerodynamic characteristics, and elevator effectiveness for the model with the 66-series wing are presented. High-speed aerodynamic characteristics of the model were improved with the 66-series wing.
    Keywords: Aerodynamics
    Type: NACA-WR-A-90
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  • 66
    Publication Date: 2018-06-05
    Description: Tests were made in the NACA two-dimensional low-turbulence tunnel of three gun ports with a height of approximately 4 percent of the chord faired into an NACA 66,2-213 low-drag-airfoil section by bulging the section at the gun port. Gun ports faired in this manner had practically no effect on the maximum lift and the critical compressibility speed of the section and showed only small increase in the drag in the range of lift coefficients for high-speed and cruising-flight conditions.
    Keywords: Aerodynamics
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  • 67
    Publication Date: 2019-06-28
    Description: An investigation of cowlings for long-nose radial engines was made on the Curtiss XP-42 fighter in the NACA full-scale wind tunnel. The unsatisfactory aerodynamic characteristics of all the cowlings with scoop inlets tested led to the development of the annular high-velocity inlet cowlings. Tests showed that ratio of cooling-air velocity at cowling inlet to stream velocity should not be less than 0.5 for this type of cowling and that critical compressibility speed can be extended to more than 500 mph at 20,000 ft altitude.
    Keywords: Aerodynamics
    Type: NACA-WR-L-241
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  • 68
    Publication Date: 2019-06-28
    Description: Correlation is established between aerodynamic characteristics of control surfaces in two-dimensional and three-dimensional flow. Slope of lift curve was affected little by overhang and balance-nose shape, but increased by sealing flap-nose gap. Effectiveness of balancing tab was same for sealed plain flap and unsealed overhang flap. Changes in hinge-moment coefficient were diminished by sealing gap. Values measured by three-dimensional flow disagreed with two-dimensional flow values until aspect ratio corrections were made.
    Keywords: Aerodynamics
    Type: NACA-WR-L-186 , NACA-ARR-L4I11F
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  • 69
    Publication Date: 2019-06-28
    Description: Characteristics are determined for various modifications of 0.155-chord blunt-nose aileron on semispan model of tapered fighter plane wing. Ailerons with 40 percent nose balance reduced high-speed stick forces. Increased balance chord increases effectiveness and reduces high-speed stick forces. Increased balance chord increases effectiveness and reduces adverse effects of gap at aileron hose. Increase of nose radii increased negative slope of curve hinge-movement coefficient plotted against deflection. Extended deflection range decreased aileron effectiveness for small deflections but increased it at large deflections. Peak pressures at noses of ailerons are relatively high at moderate deflections.
    Keywords: Aerodynamics
    Type: NACA-WR-L-262
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  • 70
    Publication Date: 2019-06-28
    Description: An investigation was made in the LMAL 7- by 10-foot wind tunnel of a NACA 23021 airfoil with a double slotted flap having a chord 32 percent of the airfoil chord (0.32c) to determine the aerodynamic section characteristics with the flaps deflected at various positions. The effects of moving the fore flap and rear flap as a unit and of deflecting or removing the lower lip of the slot were also determined. Three positions were selected for the fore flap and at each position the maximum lift of the airfoil was obtained with the rear flap at the maximum deflection used at that fore-flap position. The section lift of the airfoil increased as the fore flap was extended and maximum lift was obtained with the fore flap deflected 30 deg in the most extended position. This arrangement provided a maximum section lift coefficient of 3.31, which was higher than the value obtained with either a 0.2566c or a 0.40c single-slotted-flap arrangement and 0.25 less than the value obtained with a 0.4c double-slotted-flap arrangement on the same airfoil. The values of the profile-drag coefficient obtained with the 0.32c double slotted flap were larger than those for the 0.2566c or 0.40c single slotted flaps for section lift coefficients between 1.0 and approximately 2.7. At all values of the section lift coefficient above 1.0, the 0.40c double slotted flap had a lower profile drag than the 0.32c double slotted flap. At various values of the maximum section lift coefficient produced by various flap defections, the 0.32c double slotted flap gave negative section pitching-moment coefficients that were higher than those of other slotted flaps on the same airfoil. The 0.32c double slotted flap gave approximately the same maximum section lift coefficient as, but higher profile-drag coefficients over the entire lift range than, a similar arrangement of a 0.30c double slotted flap on an NACA 23012 airfoil.
    Keywords: Aerodynamics
    Type: NACA-WR-L-7 , NACA-ARR-L4J05
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  • 71
    Publication Date: 2019-06-28
    Description: Results of subject tests indicate the difficulty of obtaining closely balanced rudder surfaces for most tail assemblies with shielded horns and maintaining a near zero rate-of-change of hinge-moment coefficient without an additional balancing device. A comparison is made between shielded and unshielded horn test results. Pressure distribution and tuft tests of flow over different shaped horns showed higher critical speed for medium-taper nosed horn. The trim tab nose shape had little effect on tab test results.
    Keywords: Aerodynamics
    Type: NACA-WR-L-516 , NACA-ACR-4C11
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  • 72
    Publication Date: 2019-06-28
    Description: Several airfoils, Including a conventional NACA 23021 and some low-drag airfoils for which the thickness had been increased to the point that they were considered doubtfully conservative with respect to separation, were investigated as smooth airfoils and after the application of a standard roughness. The results show some of the airfoils to be critical to separation resulting from such flow disturbances. It is concluded, pending the further investigation of separation difficulties, that airfoil sections falling definitely within the conservative range should be used.
    Keywords: Aerodynamics
    Type: NACA-WR-L-659
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  • 73
    Publication Date: 2019-06-28
    Description: Wind-tunnel tests, investigating low drag wing performance in small-scale tests, showed a large increase in minimum drag coefficient, and a decrease of maximum lift coefficient occurred with decreasing Reynolds Number above certain designated values. The lift-curve slope varied up to 6% between high and low turbulence levels. Low Reynolds Number test data are unreliable for low drag airfoils either to estimate full-scale characteristics or to determine merits of airfoils for higher Reynolds numbers.
    Keywords: Aerodynamics
    Type: NACA-WR-L-138 , NACA-ACR-L4H11
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  • 74
    Publication Date: 2019-06-28
    Description: Tests were conducted at dynamic pressure of 50 lb per square foot with lift drag and pitch moment measurements throughout useful angle of attack range for constant flap deflection and position of a low-drag airfoil. Two slots were investigated and practical flap paths were selected for each Slot shape had a negligible effect on the maximum lift coefficient flap deflected, the rounded-entry slot had lower profile drag.
    Keywords: Aerodynamics
    Type: NACA-WR-A-80 , NACA-MR-A4L28
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  • 75
    Publication Date: 2019-06-28
    Description: The effects of mass distribution on lateral stability and control characteristics of an airplane have been determined by flight tests of a model in the NACA free-flight tunnel. In the investigation, the rolling and yawing movements of inertia were increased from normal values to values up to five times normal. For each moment-of-inertia condition, combinations of dihedral and vertical-tail area representing a variety of airplane configurations were tested. The results of the flight tests of the model were correlated with calculated stability and control characteristics and, in general, good agreement was obtained. The tests showed the following effects of increased rolling and yawing moments of inertia: no appreciable change in spiral stability; reductions in oscillatory stability that were serious at high values of dihedral; a reduction in the sensitivity of the model to gust disturbances; and a reduction in rolling acceleration provided by the ailerons, which caused a marked increase in time to reach a given angle of bank. The general flight behavior of the model became worse with increasing moments of inertia but, with combinations of small effective dihedral and large vertical-tail area, satisfactory flight characteristics were obtained at all moment-of-inertia conditions.
    Keywords: Aerodynamics
    Type: NACA-WR-L-388 , NACA-ARR-3H31
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  • 76
    Publication Date: 2019-06-28
    Description: This report is based on a study made by the writer as a member of the Special Committee on Design of Army Semirigid Airship RS-1 appointed by the National Advisory Committee for Aeronautics. The increasing interest in airships has made the problem of the potential flow of a fluid about an ellipsoid of considerable practical importance. In 1833 George Green, in discussing the effect of the surrounding medium upon the period of a pendulum, derived three elliptic integrals, in terms of which practically all the characteristics of this type of motion can be expressed. The theory of this type of motion is very fully given by Horace Lamb in his "Hydrodynamics," and applications to the theory of airships by many other writers. Tables of the inertia coefficients derived from these integrals are available for the most important special cases. These tables are adequate for most purposes, but occasionally it is desirable to know the values of these integrals in other cases where tabulated values are not available. For this reason it seems worth while to assemble a collection of formulae which would enable them to be computed directly from standard tables of elliptic integrals, circular and hyperbolic functions and logarithms without the need of intermediate transformations. Some of the formulae for special cases (elliptic cylinder, prolate spheroid, oblate spheroid, etc.) have been published before, but the general forms and some special cases have not been found in previous publications. (author)
    Keywords: Aerodynamics
    Type: NACA-TR-210
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  • 77
    facet.materialart.
    Unknown
    In:  CASI
    Publication Date: 2019-06-28
    Description: The design of complicated structures often presents problems of extreme difficulty which are frequently insoluble. In many cases, however, the solution can be obtained by tests on suitable models. These model tests are becoming so important a part of the design of new engineering structures that their theory has become a necessary part of an engineer's knowledge. For balloons and airships water models are used. These are models about 1/30 the size of the airship hung upside down and filled with water under pressure. The theory shows that the stresses in such a model are the same as in the actual airship. In the design of the Army Semirigid Airship RS-1 no satisfactory way was found to calculate the stresses in the keel due to the changing shape of the bag. For this purpose a water model with a flexible keel was built and tested. This report gives the theory of the design, construction, and testing of such a water model.
    Keywords: Aerodynamics
    Type: NACA-TR-211
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  • 78
    Publication Date: 2019-06-28
    Description: In the first article, in connection with a lecture on the hydrodynamic basis of flight and the potential flow about a Joukowski wing, the pressure distribution on several wings is computed and plotted. The diagrams of the pressure distributions are presented accompanied with a qualitative discussion of the pressure distribution. In the second article, the the cross-sectional outline (or profile) a Joukowski wing are plotted.
    Keywords: Aerodynamics
    Type: NACA-TM-336
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  • 79
    Publication Date: 2019-06-28
    Description: Investigations of strengths of hot wires at high velocities were conducted with platinum, nickel, and tungsten at approximately 200 Degrees Celcius hot-wire temperature. The results appear to disqualify platinum for velocities approaching the sonic range; whereas nickel withstands sound velocity, and tungsten may be used for supersonic velocities under standard atmospheric conditions. Hot wires must be supported by rigid prolongs at high velocities to avoid wire breakage. Resting current measurements for constant temperature show agreement with King's relation.
    Keywords: Aerodynamics
    Type: NACA-TN-880
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  • 80
    Publication Date: 2019-06-28
    Keywords: AERODYNAMICS
    Type: NASA-TM-101182 , NACA-ACR-4H24 , NAS 1.15:101182
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  • 81
    Publication Date: 2019-07-12
    Description: This report gives the results of tests on a rectangular wing model with a 20% full spun split flap, conducted on the whirling arm at the Daniel Guggenheim Airship Institute in Akron, Ohio. The effect of a ground board on the lift and pitching moment was measured. The ground board consisted of an inclined ramp rising up in the test channel to a level floor extending for some distance parallel to the model path. The path of the wing model with respect to the ground board accordingly represented with comparative exactness an airplane coming in for a landing. The ground clearances over the level portion of the board varied from 0 6 to 1,6 chord lengths. Results are given in the standard dimensionless coefficients plotted versus angle of attack for a particular ground clearance. The effect of the ground board is to increase the lift coefficient for a given angle of attack all the way up the stall. The magnitude of the increase varies both with the ground clearance and the angle of attack. The effect on the pitching moment coefficient is not so readily apparent due to experimental difficulties but, in general, the diving moment increases over the ground board. This effect is apparent principally at the high angles of attack. An exception to this effect occurs with flaps deflected at the lowest ground clearance (0.6 chords). Here the diving moment decreases over the ground board.
    Keywords: Aerodynamics
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  • 82
    Publication Date: 2019-07-12
    Description: At the present time there is considerable demand for improvement in the aerodynamic characteristics of cowlings for radial air-cooled aircraft engines. During the past year, numerous cowling arrangements have been investigated in various departments of the NACA laboratory. Although a few full-scale investigation have been carried out, most of the studies have been preliminary in nature and have been confined to the investigation of model arrangement in wind tunnels. Because of the existing national emergency it appears advisable to release immediately to the aircraft industry the information available on the more promising of the arrangements that have been studied. An investigation having as its aim the improvement in performance and flying qualities of single-engine air-cooled military pursuit airplanes is being conducted in the NACA 10-foot pressure wind tunnel. As a part of that investigation, studies have been made of the relative merits of a conventional NACA open-nose cowling arrangement and of a less conventional but better streamline NACA high-speed cowling arrangement in which the cooling air enters the cowling through an opening ahead of the propeller, passes internally through an element of the cowling which rotates with the propeller, and thence past the engine cylinders to the exit at the rear of the engine. These investigations indicate that at airplane speeds of around 400 miles per hour there is not a great deal to be gained in high-speed performance through the application of the latter cowling arrangement, but at speeds in excess of about 450 miles per hour a very appreciable gain is indicated. Present indications are that improved engine cooling can be obtained throughout the speed range as well as ground cooling through the use of the high-speed cowling. This paper summarizes the results obtained from wind-tunnel tests of models of the two cowling arrangements.
    Keywords: Aerodynamics
    Type: HQ-E-DAA-TN59228
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  • 83
    Publication Date: 2019-06-27
    Keywords: AERODYNAMICS
    Type: NACA-ACR-3129 , NASA-TM-79962
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  • 84
    Publication Date: 2019-06-27
    Keywords: AERODYNAMICS
    Type: NACA-ACR-244
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  • 85
    Publication Date: 2019-06-28
    Keywords: AERODYNAMICS
    Type: NACA-SR-211
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  • 86
    Publication Date: 2019-06-27
    Keywords: AERODYNAMICS
    Type: NASA-TM-79834 , NACA-ACR-4B29 , L-521
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  • 87
    Publication Date: 2019-06-27
    Keywords: AERODYNAMICS
    Type: NASA-TM-79875 , NACA-MR-L4L18
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  • 88
    Publication Date: 2019-06-27
    Keywords: AERODYNAMICS
    Type: NASA-TM-79829 , NACA-CB-L4G17 , L-141
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  • 89
    Publication Date: 2019-06-27
    Keywords: AERODYNAMICS
    Type: NASA-TM-79837 , NACA-ACR-L4E31 , L-139
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  • 90
    Publication Date: 2019-07-12
    Description: In this report a method is presented for the calculation of the profile drag of airfoil sections. The method requlres only a knowledge of the theoretical velocity distribution and can be applied readily once this dlstribution is ascertained. Comparison of calculated and experimental drag characteristics for several airfoils shows a satisfactory agreement. Sample calculatlons are included.
    Keywords: Aerodynamics
    Type: NACA ACR No. 4B05
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  • 91
    Publication Date: 2019-07-12
    Description: Investigations of the pressure distribution, the profile drag, and the location of transition for a 30-inch-chord 25-percent-thick N.A,C.A. 45-125 airfoil were made in the N.A.C.A 8-foot high-speed wind tunnel for the purpose of aiding in the development of a thick wing for high-speed airplanes. The tests were made at a lift coefficient of 0.1 for Reynolds Numbers from 1,750,000 to 8,690,000, corresponding to speeds from 80 to 440 miles per hour at 59 F. The effect on the profile drag of fixing the transition point was also investigated. The effect of compressibility on the rate of increase of pressure coefficients was found to be greater than that predicted by a simplified theoretical expression for thin wings. The results indicated that, for a lift coefficient of 0.1, the critical speed of the N.A.C,A. 45-125 airfoil was about 460 miles per hour at 59 F,. The value of the profile-drag coefficient at a Reynolds Number of 4,500,000 was 0.0058, or about half as large as the value for the N.A,C,A. 0025 airfoil. The increase in the profile-drag coefficient for a given movement of the transition point was about three times as large as the corresponding increase for the N.A.C,A. 0012 airfoil. Transition determinations indicated that, for Reynolds Numbers up to ?,000,000, laminar boundary 1ayers were maintained over approximately 40 percent of the upper and the lower surfaces of the airfoil.
    Keywords: Aerodynamics
    Type: NACA-SR-138
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  • 92
    Publication Date: 2019-08-17
    Description: This report deals with the development of a method which gives a lucid and convenient solution of the flow conditions in the vicinity of a common, thick airfoil section wherein the thickness of the profile is taken into account. The method consists in making the airfoil the streamline in a parallel flow by disposing on its mean line certain source and vortex distributions the fields of which are superposed on the parallel flow. These distributions of singularities are secured for the generalized Karman-Trefftz profile by means of conformal transformation from the flow about a circle. Five different distribution functions are afforded for the density of superposition, which combine in a specified manner to the necessary distributions of singularity and represent a generalized Karman-Trefftz profile in parallel flow. For these profiles the speed for each of the five distributions is then computed independently of the angle of attack.
    Keywords: Aerodynamics
    Type: NACA-TM-1023
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  • 93
    Publication Date: 2019-08-14
    Description: Wing pressure distribution diagrams for several angles of attack and flap deflections of 0 degrees, 20 degrees, and 40 degrees are presented. The normal force coefficients agree with lift coefficients obtained in previous test of the same model, except for the maximum lifts with flap deflection. Pressure distribution measurements were made at Reynolds Number of about 6,000,000.
    Keywords: Aerodynamics
    Type: NACA-WR-L-678
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  • 94
    Publication Date: 2019-08-07
    Description: At the request of the Army Air Forces, Materiel Command, tests were made in the two-Dimensional low-turbulence tunnel of a mode l submitted by Bell Aircraft Corporation as the tip section of the wing of the xp-63 airplane. " The model was a NACA 66, 2x-2l6 a = 0.6 airfoil section of 50-inch chord and made of dural according to standard sheet-metal practice. The model was fitted for an internal-balance aileron with a tab and a Frise type aileron. Several alterations of the skirts and balance on the internal- balance aileron were tested to obtain the various aerodynamic characteristics of the aileron.
    Keywords: Aerodynamics
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  • 95
    facet.materialart.
    Unknown
    In:  CASI
    Publication Date: 2019-07-13
    Description: In many studies, especially of nonstationary flight motion, it is necessary to determine the angular velocities at which the airplane rotates about its various axes. The three-component recorder is designed to serve this purpose. If the angular velocity for one flight attitude is known, other important quantities can be derived from its time rate of change, such as the angular acceleration by differentiations, or - by integration - the angles of position of the airplane - that is, the angles formed by the airplane axes with the axis direction presented at the instant of the beginning of the motion that is to be investigated.
    Keywords: Aerodynamics
    Type: NACA-TM-1065 , Luftwissen; 5; 8; 297-298
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  • 96
    Publication Date: 2019-07-13
    Description: The wall interference is obtained for a wind tunnel of elliptic section for the two cases of closed and open working sections. The approximate and exact methods used gave results in practically good agreement. Corresponding to the result given by Glauert for the case of the closed rectangular section, the interference is found to be a minimum for a ratio of minor to major axis of 1:square root of 6 This, however, is true only for the case where the span of the airfoil is small in comparison with the width of the tunnel. For a longer airfoil the favorable ellipse is flatter. In the case of the open working section the circular shape gives the minimum interference.
    Keywords: Aerodynamics
    Type: NACA-TM-1075 , Journal of the Society of Mechanical Engineers; 36; 190; 123-127
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  • 97
    facet.materialart.
    Unknown
    In:  CASI
    Publication Date: 2019-07-13
    Description: The present report deals with a number of problems, particularly with the interaction of the fuselage with the wing and tail, on the basis of simple calculating method's derived from greatly idealized concepts. For the fuselage alone it affords, in variance with potential theory, a certain frictional lift in yawed flow, which, similar to the lift of a wing of small aspect ratio, is no longer linearly related to the angle of attack. Nevertheless there exists for this frictional lift something like a neutral stability point the position of which on oblong fuselages appears to be associated with the lift increase of the fuselage in proximity to the zero lift, according to the present experiments. The Pitching moments of the fuselage can be determined with comparatively great reliability so far as the flow conditions in the neighborhood of the axis of the fuselage can be approximated if the fuselage were absent, which, in general, is not very difficult. For the unstable contribution of the fuselage to the static longitudinal stability of the airplane it affords comparatively simple formulas, the evaluation of which offers little difficulty. On the engine nacelles there is, in addition a very substantial wing moment contribution induced by the nonuniform distribution of the transverse displacement flow of the nacelle along the wing chord; this also can be represented by a simple formula. A check on a large number of dissimilar aircraft types regarding the unstable fuselage and nacelle moments disclosed an agreement with the wind-tunnel tests, which should be sufficient for practical requirements. The errors remained throughout within the scope of instrumental accuracy.
    Keywords: Aerodynamics
    Type: NACA-TM-1036 , Luftfahrtforschung; 18; 3-Feb; 52-56
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  • 98
    Publication Date: 2019-07-11
    Description: The wide use of diffusers, in various fields of technology, has resulted in several experimental projects to study the action and design of diffusers. Most of the projects dealt with steam (steam turbine nozzles). But diffusers have other applications - that is, ventilators, smoke ducts, air coolers, refrigeration, drying, and so forth. At present there is another application for diffusers in wind-tunnel design. Because of higher requirements and increased power of such installations more attention must be paid to the correctness of work and the decrease in losses due to every section of the tunnel. A diffuser, being one of the component parts of a tunnel , can in the event of faulty construction introduce considerable losses. Therefore, in the design of the new CAHI wind tunnel, it was suggested that an experimental study of diffusers be made, with a view to applying the results to wind tunnels. The experiments conducted by K. K. Baulin in the laboratories of CAHI upon models of diffusers of different cross sections, lengths, and angles of divergence, were a valuable source of experimental data. They were of no help, however, in reaching any conclusion regarding the optimum shape because of the complexity and diversity of the factors which all appeared simultaneously, thereby precluding the.study of the effects of any one factor separately. On the suggestion of the director of the CAHI,Prof. B. N. Ureff, it was decided to experiment on a two-dimensional diffuser model and determine the effect, of the angle of divergence. The author is acquainted with two experimental projects of like nature: the first was conducted with water, the other with air. The first of these works, although containing a wealth of experimental data, does not indicate the nature of flow or its relation to the angle of divergence. The second work is limited to four angles - that is, 12 deg, 24 deg, 45 deg, 90 deg. The study of this diffuser did not supply any information about the effect of smaller angles which, because of their advantages, are more commonly used, The author was able to acquaint himself with the second work only after the experiments were started. For these reasons, as well as because on the basis of those works no conclusion can be reached regarding the nature of flow distribution, of eddies, and so forth, experimental work was continued. The need for determining flow patterns follows from the fact that from them are determined methods of measurement - that is, the determination of velocities by means of the pitot tube, which, as is well known, gives correct indications only when placed with its axis parallel to the axis of flow. The data contained in this report were obtained from experiments conducted by the Aerodynamical Laboratories of the CAHI. The solutions to some. of the mathematical problems connected with the experiments are due to Prof. S. A, Chapligin.
    Keywords: Aerodynamics
    Type: NACA-TM-1059 , Report of the Central Aero-Hydrodynamical Inst., Moscow; Rept-21
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  • 99
    Publication Date: 2019-07-12
    Description: Preliminary data are presented on the variation of the maximum lift coefficient with Mach number. The data were obtained from tests in the 8-foot high-speed tunnel of three NACA 16-series airfoils of 1-foot chord. Measurements consisted primarily of pressure-distribution measurements in order to illustrate the nature of the phenomena. It was found that the maximum lift coefficient of airfoils is markedly affected by compressibility even at Mach numbers as low as 0.2. At high Mach numbers pronounced decrease of the maximum lift coefficient was found. The magnitude of the effects of compressibility on the maximum lift coefficient and the low speeds at which these effects first appear indicate clearly that consideration of the take-off thrust for propellers will give results seriously in error if these considerations are based on the usual low-speed maximum-lift-coefficient data generally used.
    Keywords: Aerodynamics
    Type: NACA-ACR-246 , NACA-SR-246
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  • 100
    Publication Date: 2019-07-12
    Description: This report covers tests of a 5-foot model of the NACA 66,2-420 low-drag airfoil at high speeds including the critical compressibility speed. Section coefficients of lift, drag, and pitching moment, and extensive pressure-distribution data are presented. The section drag coefficient at the design lift coefficient of 0.4 increased from 0.0042 at low speeds to 0.0052 at a Mach number of 0.56 (390 mph at 25,000 ft altitude). The critical Mach number was about 0.60. The results cover a Reynold number range from 4 millions to 17 millions.
    Keywords: Aerodynamics
    Type: NACA-ACR-234 , NACA-SR-234
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