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  • Other Sources  (66)
  • Aircraft Design, Testing and Performance  (31)
  • Ertrag  (17)
  • Kartoffeln  (11)
  • Umweltmedizin  (7)
  • Inorganic Chemistry
  • ddc:554.3
  • 1980-1984
  • 1945-1949  (32)
  • 1935-1939  (12)
  • 1920-1924  (17)
  • 1915-1919  (5)
  • 1948  (32)
  • 1938  (12)
  • 1924  (6)
  • 1923  (4)
  • 1921  (7)
  • 1918  (2)
  • 1916  (2)
  • 1915  (1)
Collection
Source
Keywords
Publisher
Language
Years
  • 1980-1984
  • 1945-1949  (32)
  • 1935-1939  (12)
  • 1920-1924  (17)
  • 1915-1919  (5)
Year
  • 1
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    Wind und Pflanzenschädlinge (1948)
    In:  Wetter und Klima 1; p.316
    Details
    Publication Date: 1948
    Description: In einem kleinen allgemeinen Kommentar wird der Zusammenhang zwischen Wind (v.a. Windrichtung) und anderen Wetterbedingungen in Verbindung mit der Ausbreitung des Kartoffelkäfers und des Borkenkäfers genannt. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland ; 1943-46 ; Kartoffeln ; Forst ; Pflanzenschädling ; Hackfrüchte
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  • 2
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    Beziehungen zwischen Niederschlagsmengen und Ernteerträgen in Niederbayern (1924)
    In:  Meterolog. Zeitschrift, Braunschweig, 41: 170-173
    Details
    Publication Date: 1924
    Description: Beziehung zwischen Niederschlag und Ertrag mithilfe der Korrelationsmethode KATASTER-BESCHREIBUNG: Berechnung von Korrelationswerten deuten auf starken Einfluss des Juniniederschlags hin, durch Berechnung der Abweichung vom 10jährigen Mittel werden Beziehungen einzelner Monate, bzw. 2 monatiger Niederschlagssummen zum Ertrag für Winterweizen, Winterroggen, Hafer, Kartoffeln, Sommerweizen und Sommerroggen sichtbar KATASTER-DETAIL: Delta Nied+ (Januar), dann Winterweizen +; Delta Nied- (〈 20mm) im März, dann Ertrag von Winterweizen, Winterroggen, Sommerroggen und Sommerweizen +; Delta Nied+ (〉60mm) im Juli, dann Ertrag Winterweizen++; Delta Nied- (〈40mm) im Juni, dann Kartoffel +, aber Hafer-; Delta Nied+ (〉130mm) im Juni, dann Kartoffel -, aber Hafer+;
    Keywords: Niederbayern ; 1884-1922 ; Kartoffeln ; Ertrag ; Hafer ; Korrelationsmethode ; Niederschlag ; Roggen ; Weizen
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  • 3
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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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  • 4
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    Die Möglichkeit der Abschätzung des Ernteertrages auf Grund meteoroloigischer Angaben. (1923)
    In:  Naturwissenschaften 11(37):769-776
    Details
    Publication Date: 1923
    Description: Beschreibung der landwirtschaftlichen Meterologie in den USA, anhand vom Beispielen (Warren-Smith, Wallace, Blair, Kincer)'Kritische Phasen' und Korrelation von Witterungsdaten mit Ertragsdaten von Mais, Weizen, Baumwolle KATASTER-BESCHREIBUNG: Einfluss der Witterung (Temperatur, Niederschlag) auf den Ertrag in verschiedenen Staaten der USA. Ausschlaggebend sind die Monate Mai, Juni, Juli und August KATASTER-DETAIL: Missouri: Delta T (Juni, Juli, August) +, dann Ertrag (Mais) +; Iowa: Delta T (Mai, Juli) + und Delta Nied (August) +, dann Ertrag (Mais) +; Nebraska: Delta T (Juli) + und Delta Nied (Mai, Juli) +, dann Ertrag (Mais) +; Indiana: Delta T (Juli) + und Delta Nied (Juli, August) +, dann Ertrag (Mais) +; Minnesota: Delta T (Juni, August) + und Delta Nied (August) +, dann Ertrag (Mais) +; Ohio: Delta T (Mai) + und Delta Nied (Juli, August) +, dann Ertrag (Mais) +; Ohio: Delta Nied (Juli, Anfang August) 〉 76mm , dann Ertrag (Mais) +; Ohio: Delta T (März) +, dann Ertrag (Winterweizen) +; Illinois: Delta T (Mai, Juli) + und Delta Nied (August) +, dann Ertrag (Mais) +; Kansas: Delta Nied (Juni, Juli, August) +, dann Ertrag (Mais) +;
    Keywords: USA ; 19. Jahrhundert ; Ertrag ; Korrelationsmethode ; Mais ; Temperatur ; Weizen ; Witterung
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  • 5
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    Witterungsverlauf und Ernteertrag in der Kurmark bei den Hauptgetreidearten und Kartoffeln. (1938)
    In:  Landwirtschaftl. Jahrbuch 86:823-924.
    Details
    Publication Date: 1938
    Description: Erarbeitung einer ausbaufähigen Methode für das Erfassen des Witterungsablaufes; Vergleichen einer Zwölfjahresreihe von Erträgen mit dem Witterungsablauf; bearbeitet wurden Winterroggen, Winterweizen, Wintergerste, Hafer, Sommergerste, Sommerweizen, Kartoffeln KATASTER-BESCHREIBUNG: Zusammenhang Witterung und Ertrag bei Getreide und Kartoffeln KATASTER-DETAIL: Delta Wasserversorgung (Frühjahr) - und Delta Wasserversorgung (Mai, Juni, Juli) +, dann Ertrag (Getreide) +; Delta T (frühe Entwicklungsstadien) -, dann Ertrag (Winterroggen, Hafer) +; Delta T (April) -, dann Ertrag (Hafer) +; Delta Nied (April, Mai) -, dann Ertrag (Winterweizen) +; delta T (Mai) -, dann Ertrag (Winterroggen) +; Delta T +, dann Ertrag (Kartoffel) +; Delta Nied (Juli, August) +, dann Ertrag (Kartoffel) +;
    Keywords: Brandenburg ; 1924-37 ; Kartoffeln ; Ertrag ; Getreide ; Witterung
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  • 6
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    Niederschlags- und Erntemengen (1915)
    In:  Deut. Landwirtschaflt. Presse 42: 420-421
    Details
    Publication Date: 1915
    Description: Korrelation der Sommer- und Winterniederschläge (Oktober-März) mit den Erträgen von Sommer- und Winterweizen, Roggen, Hafer, Gerste, Zuckerrüben und Kartoffeln, Winterniederschläge sind entscheidend für die Erträge, aber ertragsrelevanter sind die Sommerniederschläge und hier nicht in der Häufigkei, sondern der Menge im Zusammenspiel mit Temperatur, Sonnenscheindauer etc. KATASTER-BESCHREIBUNG: Beziehung zwischen der Niederschlagshöhe und dem Ertrag verschiedener Kulturen, getrennt für Winter- und Sommerniederschläge als Grafiken KATASTER-DETAIL:
    Keywords: Schlesien und Sachsen-Anhalt ; 1888-1907 ; Zuckerrüben ; Kartoffeln ; Ertrag ; Getreide ; Korrelationsmethode ; Niederschlag ; Roggen ; Weizen
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  • 7
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    Der Einfluss des Klimas auf die Erhaltung des Landwirtschaftsbetriebes in der Provinz Sachsen (1923)
    In:  Diss. Leipzig.
    Details
    Publication Date: 1923
    Description: Einfluss von Boden und Klima auf die Höhe der Erträge, Einteilung in verschiedene Landbaubezirke KATASTER-BESCHREIBUNG: Anteil der Hauptfrüchte an den Bodennutzung, "Gedeihen" und Beziehung zum Klimaertrag in Landbaukreisen, Details Seite 183, Einfluss der Witterung auf die Ernten in den einzelnen Jahren KATASTER-DETAIL:
    Keywords: Sachsen ; 1881-1910 ; Ertrag ; Getreide ; Witterung
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  • 8
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    Die Bodenverhältnisse Schlesiens in ihrer Einwirkung auf das Anbauverhältnis und die Ernteerträge der Kulturpflanzen (1923)
    In:  Diss. Breslau.
    Details
    Publication Date: 1923
    Description: Beziehung Witterung und Ertragshöhe KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Schlesien ; Ertrag ; Witterung
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  • 9
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    Malariaepidemien in Norddeutschland nach dem zweiten Weltkrieg unter besonderer Berücksichtigung der autochthonen Malaria (1948)
    In:  Dissertation, Hamburg
    Details
    Publication Date: 1948
    Description: Mehrzahl der autochthonen Malariaerregerübertragungen auf dem Gebiet von Brandenburg KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Norddeutschland ; 1939-1947 ; Umweltmedizin ; Infektionskrankheiten
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  • 10
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    Einheimische Malaria und Anophelismus in der Nachkriegszeit (1948)
    In:  Deutsche Medizinische Wochenschrift 73, 515-518
    Details
    Publication Date: 1948
    Description: Anthropogene Veränderungen der Umweltbedingungen von Anophelesmücken KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland ; Umweltmedizin ; Infektionskrankheiten
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  • 11
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    Experimentelle Untersuchungen über die die Malariainfektion des Anopheles und des Menschen beeinflussenden Umstände (1921)
    In:  Beihefte zum Archiv für Schiffs- und Tropenhygiene 25 () Beiheft 2
    Details
    Publication Date: 1921
    Description: Temperaturabhängigkeit von Malariaerregern in einheimischen Anophelesmücken KATASTER-BESCHREIBUNG: optimale Generation-Entwicklung bei einer permanenten Außentemperatur von 24-30°C, unter 15-16°C keine Entwicklung KATASTER-DETAIL:
    Keywords: Europa ; 1901-1903 ; Umweltmedizin ; Infektionskrankheiten
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  • 12
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    Bemerkungen zur gegenwärtigen Malarialage in Deutschland (1948)
    In:  Ärztliche Wochenschrift 3, 56-59
    Details
    Publication Date: 1948
    Keywords: Deutschland ; Umweltmedizin ; Infektionskrankheiten
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  • 13
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    Körner- und Kartoffelerträge auf leichtem Sandboden. (1918)
    In:  Deutsche Landwirtschaftliche Presse 45:287-288.
    Details
    Publication Date: 1918
    Description: Einfluss des Niederschlages auf die Höhe der Ertrages bei Getreide und Kartoffeln auf leichtem Sandboden KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Brandenburg ; 1910-1917 ; Kartoffeln ; Ertrag ; Niederschlag ; Trockenheit
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  • 14
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    Grundzüge der Bioklimatik des Menschen (1938)
    In:  Klima - Wetter - Mensch, Woltereck, H. (Hrsg.), Verlag von Quelle und Meyer, Lepzig, S.127-229
    Details
    Publication Date: 1938
    Description: Bioklimatik einzelner Klimaelemente, atmosphärischer Zustände und Vorgänge KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Umweltmedizin
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  • 15
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    Hat das Wetter einen Einfluss auf die Form der Kartoffelknolle? (1921)
    In:  Die Kartoffel, S. 90
    Details
    Publication Date: 1921
    Description: Zusammenhang Niederschlag und Wachstum der Kartoffelknolle KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Kartoffeln ; Ertrag ; Niederschlag ; Trockenheit
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  • 16
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    Einfluß der klimatischen Faktoren auf die Höhe und Güte der Ernteertäge Preußens. Nachgewiesen an Hand der preußischen Erntestatistik der letzten 40 Jahre (1924)
    In:  Diss. Breslau
    Details
    Publication Date: 1924
    Description: Einteilung der Vegetationszeit in 5-6 Perioden und Vergleich von 5-Jahresmitteln des Ertrages mit Jahren gleicher Jahreswitterungen KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Preußen ; 1924 ; Ertrag ; Vegetationsperiode ; Witterung
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  • 17
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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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  • 18
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    Grundriss einer Meteorobiologie (1938)
    In:  Verlag von Julius Springer, Berlin
    Details
    Publication Date: 1938
    Description: Meteorotrope Krankheiten, Saisonkrankheiten KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Umweltmedizin
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  • 19
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    Der Einfluss der Witterung auf die Reifezeit usw. (1921)
    In:  Die Kartoffel, Seite 136
    Details
    Publication Date: 1921
    Description: Zusammenhang zwischen der Witterung und der Reifezeit der Kartoffelknolle KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Kartoffeln ; Ertrag ; Witterung
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  • 20
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    Über den Einfluß des Regens auf die Höhe der Pflanzenerträge. (1948)
    In:  Zeitschrift für Pflanzenernährung, Düngung, Bodenkunde 42:5-11.
    Details
    Publication Date: 1948
    Description: Bedeutung Niederschlag und Ertrag KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland ; Ertrag ; Niederschlag
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  • 21
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    Beziehungen zwischen Niederschlagsmenge und Ernteertrag in Niederbayern (1924)
    In:  Meteorologische Zeitschrift 41:170-173.
    Details
    Publication Date: 1924
    Description: Ausgehend von Witterungsfaktoren werden Monate bzw. Monatsgruppen beschrieben, die besonders ausschlaggebend für die Erträge sind KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Niederbayern ; 1920 ; Ertrag ; Getreide ; Landwirtschaft ; Niederschlag ; Temperatur ; Witterung
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  • 22
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    Eine Methode zur quantitativen Erfassung der Zusammenhänge zwischen Wetterablauf und Ernteertrag (1948)
    In:  Annalen der Meteorologie, S. 326-328.
    Details
    Publication Date: 1948
    Description: Entwicklung eines "Wetterschadensfaktor", der Zusammenhang zwischen Witterung und Ernteertrag beschreibt KATASTER-BESCHREIBUNG: - KATASTER-DETAIL: -
    Keywords: Schleswig-Holstein ; 1933-42 ; Kartoffeln ; Ertrag ; Korrelationsmethode ; Landwirtschaft ; Niederschlag ; Temperatur ; Witterung
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  • 23
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    Beziehung zwischen Reifedauer des Einterroggens und den Temperaturhöchstwerten (1916)
    In:  Landw. Jahrbuch für Bayern.
    Details
    Publication Date: 1916
    Description: Einfluß der Temperatur auf die Phänologie des Roggens KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Bayern ; Ertrag ; Phänologie ; Roggen ; Temperatur
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  • 24
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    Pflanzliche Schädlinge landwirtschaftlicher Kulturpflanzen. In: Pflanzenschutz und Landwirtschaft - Zwei Vorträge (Herausg.: Wehner, H.) (1921)
    In:  Schriften der oekonomischen Gesellschaft im Freistaat Sachsen 8; No.3; p.1-24
    Details
    Publication Date: 1921
    Description: Diskussion einiger wichtiger Pflanzenkrankheiten im Ackerbau, wie z.B. Brandkrankheiten verschiedener Kulturen und verschiedenen Kartoffelkrankheiten. Gestützt werden die Anmerkungen von regionalen Beispielen aus Deutschland. Teilweise wird Bezug zum Wetter hergestellt. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland ; 1920-1921 ; Kartoffeln ; Getreide ; Pflanzenkrankheit ; Hackfrüchte
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  • 25
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    An investigation on the relation between the weather conditions and the occurrence of potato blight (Phytophthora infestans); and of the qualities that determine the degree of susceptibility of the tubers for this disease (1924)
    In:  129 p.
    Details
    Publication Date: 1924
    Description: Untersuchung der Zusammenhänge zwischen Wetter und Befall von Kartoffelpflanzen mit Phytophthora infestans in teils Feld- teils Laborversuchen. Weitere Untersuchungen zu Bekämpfungsmaßnahmen. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Niederlande ; 1919-1923 ; Kartoffeln ; Pflanzenkrankheit
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  • 26
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    The effect of frost and decay upon the starch in potatoes (1918)
    In:  Jour. industr. and engin. Chem. 10; p.725-726
    Details
    Publication Date: 1918
    Description: Laborversuche zur Untersuchung des Zusammenhangs zwischen Frosteinwirkung und Fäulebefall auf die Speisestärke der Kartoffel KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Labor ; 1916-18 ; Kartoffeln ; Pflanzenkrankheit
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  • 27
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    Klima und Krankheitserreger (1938)
    In:  Klima - Wetter - Mensch, Woltereck, H. (Hrsg.), Verlag von Quelle und Meyer, Lepzig, S.253-296
    Details
    Publication Date: 1938
    Description: Seuchenerreger und -überträger und der Einfluss von Temperatur, Feuchtigkeit und Jahresschwankungen KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Umweltmedizin
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  • 28
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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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  • 29
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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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    NASA TECHNICAL REPORTS
  • 30
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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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    NASA TECHNICAL REPORTS
  • 31
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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
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  • 32
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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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  • 33
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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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  • 34
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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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  • 35
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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
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  • 36
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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
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  • 37
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    Preliminary Results of British Nene II Engine Altitude-Chamber Performance Investigation. I - Altitude Performance Using Standard 18.75-Inch-Diameter Jet Nozzle (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation is being conducted to determine the altitude performance characteristics of the British Nene II engine and its components. The present paper presents the preliminary results obtained using a standard jet nozzle. The test results presented are for conditions simulating altitudes from sea level to 60,000 feet and ram pressure ratios from 1.0 to 2.3. These ram pressure ratios correspond to flight Mach numbers between zero and 1.16 assuming a 100 percent ram recovery.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E8E12
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  • 38
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    Design Data for Graphical Construction of Two-Dimensional Sharp-Edge-Throat Supersonic Nozzles (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Design data are presented for the graphical construction of two-dimensional sharp-edge-throat supersonic nozzles of minimum length for test-section Mach numbers from 1.20 to 10.00. The method of characteristics used in the design is briefly reviewed.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E8J12
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  • 39
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    Experimental Pressure Distribution on Fuselage Nose and Pilot Canopy of Supersonic Airplane at Mach Number 1.90 (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An investigation of the pressure distribution on the fuselage nose and the pilot canopy of a supersonic airplane model has been conducted at a Mach number of 1.90 over a wide range of angles of attack and yaw. Boundary layer separation apparently occurred from the upper surface at angles of attack above 24 degrees and from the lower surface at minus 15 degrees. No separation from the sides of the fuselage was evident at yaw angles up to 12 degrees.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E8I07
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  • 40
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    Free-Spinning, Longitudinal-Trim, and Tumbling Characteristics of a 1/20-Scale Model of the Consolidated Vultke MX-813 (Prototype of XP-92) Airplane as Determined in the Langley 20-Foot Free-Spinning Tunnel (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation has been conducted in the Langley 20-foot free-spinning tunnel to evaluate the spin, longitudinal-trim, and tumbling characteristics of a 1/20-scale model of the Consolidated Vultee MX-813 airplane. The effects of control position were determined for the model ballasted to represent the airplane in its design gross weight loading. The model, in general, would not spin but demonstrated a tendency to trim at very high stalled angles of attack. Static tests substantiated the dynamic tests as regards the trim characteristics. Movement of the elevator, however, from up to slightly down was effective in pitching the model from stalled to normal trim attitudes. The model would not tumble.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL8G26
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  • 41
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    Summary of Section Data on Trailing-Edge High-Lift Devices (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A summary has been made of available data on the characteristics of airfoil sections with trailing-edge high-lift devices. Data for plain, split, and slotted flaps are collected and analyzed. The effects of each of the variables involved in the design of the various types of flap are examined and, in cases where sufficient data are given, optimum configurations are deduced. Wherever possible, the effects of airfoil section, Reynolds number, and leading-edge roughness are shown. For single and double slotted flaps, where a great mass of unrelated date are available, maximum lift coefficients of a large number of configurations are presented in tables.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L8D09
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  • 42
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    Comparison of Drop and Wind-Tunnel Experiments on Bomb Drag at High Subsonic Speeds (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The drag coefficients of bombs at high velocities velocity of fall was 97 percent of the speed of sound) (the highest are determined by drop tests and compared with measurements taken in the DVL high-speed closed wind tunnel and the open jet at AVA - Gottingen.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1186 , Deutsche Luftfahrtforschung Forschungsbericht; Rept-1570
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  • 43
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    Preliminary Fatigue Studies on Aluminum Alloy Aircraft Girders (1938)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Preliminary information on the complex subject of the fatigue strength of fabricated structural members for aircraft is presented in the test results obtained on several different types of airship girders subjected to axial tension and compression in a resonance fatigue machine. A description of this machine as well as numerous photographs of the fatigue failures are given. There is also presented an extended bibliography on the subject of fatigue strength.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-637
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  • 44
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    The Influence of Dimensional Modifications upon the Spin and Recovery Characteristics of a Tailless Airplane Model Having Its Wings Swept Forward 15 Deg (Cornelius XFG-1) (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation has been conducted in the Langley 20-foot free- spinning tunnel scale model of the Cornelius XFG-1 glider, a tailless design having its wings swept forward 15 degrees. It was previously found to possess erratic spin and recovery characteristics, and tests were made to determine modifications which would lead to normal steady spins with consistently good recoveries. The results of the investigation indicated that modifications that aid not appreciably alter the basic design aid not appreciably improve the spin and recovery characteristics. In this instance it appears that the sweptforward wing is the cause of unsatisfactory spin and recovery characteristics.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL8H17
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  • 45
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    Preliminary Full-Scale Wind-Tunnel Investigation of Wing Ducts for Radiators, Special Report (1938)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Wing ducts for liquid-cooled engine radiators have been investigated in the N.A.C.A. full-scale wind tunnel on a large model airplane. Th e tests were made to determine the relative merits of several types of duct and radiator installations for an airplane of a particular des ign. In the test program the principal duct dimensions were system atically varied, and the results are therefore somewhat applicable to the general problems of wing duct design, although they should be co nsidered as preliminary and only indicative of the inherent possibil ities.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-88
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  • 46
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    Wind-Tunnel Investigation of Air Inlet and Outlet Openings for Aircraft, Special Report (1938)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation was made in the NACA 5-foot vertical wind tunnel of a large variety of duct inlets and outlets to obtain information relative to their design for the cooling or the ventilation systems on aircraft. Most of the tests were of openings in a flat plate but, in order to determine the best locations and the effects of interference, a few tests were made of openings in an airfoil. The best inlet location for a system not including a blower was found to be at the forward stagnation point; for one including a blower, the best location was found to be in the region of lowest total head, probably in the boundary layer near the trailing edge. Design recommendations are given, and it is shown that correct design demands a knowledge of the external flow and of the internal requirements in addition to that obtained from the results of the wind tunnel tests.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-95
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  • 47
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    Full-Scale Wind-Tunnel Investigation of Wing Cooling Ducts, Special Report (1938)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The systematic investigation of wing cooling ducts at the NACA laboratory has been continued with tests in the full-scale wind tunnel on ducts of finite span. These results extend the previous investigation on section characteristics of ducts to higher Reynolds numbers and indicate the losses due to the duct ends. The data include comparisons between ducts completely within the ring and the conventional underslung ducts. Methods of flow regulation were studied and data were obtained for a wide range of internal duct resistance. The results show satisfactory correlation between the finite span and the previously measured section characteristics obtained with full-span ducts. The effects of the various design parameters on the duct characteristics are discussed. The cooling power required for the internal duct installation is shown to be only a small percentage of the engine power.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-94
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  • 48
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    Investigation in the 7-By-10 Foot Wind Tunnel of Ducts for Cooling Radiators Within an Airplane Wing, Special Report (1938)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation was made in the NACA 7- by 10-foot wind tunnel of a large-chord wing model with a duct to house a simulated radiator suitable for a liquid-cooled engine. The duct was expanded to reduce the radiator losses, and the installation of the duct and radiator was made entirely within the wing to reduce form and interference drag. The tests were made using a two-dimensional flow set-up with a full-span duct and radiator. Section aerodynamic characteristics of the basic airfoil are given and also curves showing the characteristics of the various duct-radiator combinations. An expression for efficiency, the primary criterion of merit of any duct, and the effect of the several design parameters of the duct-radiator arrangement are discussed. The problem of throttling is considered and a discussion of the power required for cooling is included. It was found that radiators could be mounted in the wing and efficiently pass enough air for cooling with duct outlets located at any point from 0.25c to 0.70c from the wing leading edge on the upper surface. The duct-inlet position was found to be critical and, for maximum efficiency, had to be at the stagnation point of the airfoil and to change with flight attitude. The flow could be efficiently throttled only by a simultaneous variation of duct inlet and outlet sizes and of inlet position. It was desirable to round both inlet and outlet lips. With certain arrangements of duct, the power required for cooling at high speed was a very low percentage of the engine power.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-93
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  • 49
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    The Torsional and Bending Deflection of Full-Scale Duralumin Propeller Blades under Normal Operating Conditions, Special Report (1938)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The torsional deflection of the blades of three full-scale duralumin propellers operating under various loading conditions was measured by a light-beam method. Angular bending deflections were also obtained as an incidental part of the study. The deflection measurements showed that the usual present-day type of propeller blades twisted but a negligible amount under ordinary flight conditions. A maximum deflection of about 1/10th of a degree was found at V/nD of 0.3 and a smaller deflection at higher values of V/nD for the station at 0.70 radius. These deflections are much smaller than would be expected from earlier tests, but the light-beam method is considered to be much more accurate than the direct-reading transit method used in the previous tests.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-84
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  • 50
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    Performance of Compressor of XJ-41-V Turbojet Engine V-Performance Analysis of Compressor with Revised Vaned Collector over Range of Compressor Speeds from 3600 to 11,500 RPM (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation of the XJ-41-V turbojet-engine compressor with a revised vaned collector was conducted to determine the performance of the compressor and to obtain fundamental information on the aerodynamic problems associated with large centrifugal compressors of this type. The original vaned collector was revised by increasing the flow area at the vaned collector entrance. A maximum adiabatic efficiency of 0.81 was obtained et a corrected weight flow of 36.5 pounds per second and a pressure ratio of 1.90. The peak pressure ratio was 3.93 and occurred at an impeller speed of 11,500 rpm at a corrected weight flow of 65.5 pounds per second. Revision of the vaned collector resulted in an increased airflow capacity over the speed range. The design air-flow capacity of 78 pounds per second was very nearly reached at the engine design speed of 11,500 rpm. The compressor air-flow choking point occurred in the vaned collector passage; however, at speeds above 8300 rpm, the air-flow capacity of the impeller was being approached as indicated by large pressure losses in the impeller at maximum air-flow conditions. An increase in compressor air-flow capacity at the higher speeds can possibly be obtained 5y removal of the flow restriction in the impeller, which would result in an increased air density at the vaned collector entrance.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SE8A22
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  • 51
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    Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: The losses in the inlet air ducts, the diffusers, and the de-icing equipment associated with turbojet engine installations cause a reduction in the total pressure at the inlet of the engine and result in reduced thrust and increased specific fuel consumption. An analytical evaluation of the effects of inlet losses on the net thrust and the fuel economy of a 3000-pound-thrust axial flow turbojet engine with a two-stage turbine is presented. The analysis is based on engine performance characteristics that were determined from experiments in the NACA Cleveland altitude wind tunnel. The experimental investigation did not include tests in which inlet losses were systematically varied, but the effects of these losses can be accurately estimated from the experimentally determined performance characteristics of the engine.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E8C16a
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  • 52
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    Flight Investigation to Determine the Aerodynamic Characteristics of Rocket-Powered Models Representative of a Fighter-Type Airplane Configuration Incorporating an Inverse-Taper Wing and a Vee Tail (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Two rocket-powered models representative of a fighter-type airplane were investigated in flight at Mach numbers up to 1.01 and 1.07 by the Langley Pilotless Aircraft Research Division at its testing station at Wallops Island, Va. These models incorporated an inverse-taper wing and a vee tail and were flown with controls undeflected and wing and stabilizer set at 0 deg incidence. Values of lateral acceleration, normal acceleration velocity, and drag were obtained by use of telemeters and a Doppler velocimeter radar unit. The results of this investigation indicated no unusual variation in the lateral acceleration characteristics. After the cessation of powered flight, the lateral oscillation quickly damped to zero. The data indicated that the airplane, at low lift coefficients, should not experience any abrupt trim changes until it attains a Mach number of 0.97. The change in normal-force coefficient associated with this trim change will amount to about 0.03 with the center of gravity located at 4.48% of the mean aerodynamic chord. At higher lift coefficients, on the basis of other data, the Mach number at which this trim change occurs would be expected to be decreased. The neutral point of the model at Mach numbers near 1.05 was estimated to fall at 45% of the mean aerodynamic chord, assuming a lift-curve slope of 0.05. A value of the static-directional-stability parameter dCn/d(psi) of approximately -0.002 was estimated for a Mach number of 0.93. The values of drag coefficient obtained from both model flights were in a good comparative agreement. The highest drag coefficient occurred at a Mach number of 1.01 and was equal to 0.044.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L8G29
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  • 53
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    Performance Investigations of a Large Centrifugal Compressor from an Experimental Turbojet Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation was conducted on a large centrifugal compressor from an experimental turbojet engine to determine the performance of the compressor and to obtain fundamental information on the aerodynamic problems associated with large centrifugal-type compressors. The results of the research conducted on the compressor indicated that the compressor would not meet the desired engine-design air-flow requirements (78 lb/sec) because of an air-flow restriction in the vaned collector (diffuser). Revision of the vaned collector resulted in an increased air-flow capacity over the speed range and showed improved matching of the impeller and diffuser components. At maximum flow, the original compressor utilized approximately 90 percent of the available geometric throat area at the vaned-collector inlet and the revised compressor utilized approximately 94 percent, regardless of impeller speed. The ratio of the maximum weight flows of the revised and original compressors were less than the ratio of effective critical throat areas of the two compressors because of the large pressure losses in the impeller near the impeller inelt and the difference increased with an increase in impeller speed. In order to further increase the pressure ratio and maximum weight flow of the compressor, the impeller must be modified to eliminate the pressure losses therein.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E8H13
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  • 54
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    N.A.C.A. Stall-Warning Device (1938)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: With some airplanes the approach to the stall is accompanied by changes in the behavior, such as tail buffeting or changes in the control characteristics of the airplane so that the pilot obtains a warning of the impending stall. Vith other airplanes it is possible to approach the stall without any perceptible warning other than the reading of the air-speed meter, in which case the danger of inadvertent stalling is considerably greater. Although it is not within the scope of this paper to discuss stalling characteristics, it is desired to point out that in general the danger of inadvertent stalling is greatest with those airplanes that behave worse when the stalling occurs; that is, with airplanes in which the stall starts at the wing tips. A warning of the impending stall is desirable in any case, but is particularly desirable with airplanes of the latter type.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-80
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  • 55
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    An Investigation of the McDonnell XP-85 Airplane in the Ames 40- by 80-foot Wind Tunnel. Force and Moment Tests (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Wind-tunnel tests of the McDonnell XP-85 airplane were conducted to determine its longitudinal, lateral, and directional stability and the characteristics of the aileron, the ruddervator, the leading-edge droop nose flap, and the stall control vanes. The directional stability of the airplane with numerous skyhook modifications and with a ventral fin was also investigated. The results of the tests showed that the effectiveness of the droop nose flaps and the stall control vanes was negligible with regard to either the maximum lift or longitudinal stability of the airplane. Contrary to any previous small-scale results, extension of the skyhook caused a 75-percent reduction in the directional stability of the airplane for both low and high values of lift coefficient. The simplest solution to the problem short of a major redesign of the skyhook appears to be the adoption of a ventral fin.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SA8I23
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  • 56
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    Performance of J-33-A-21 Turbojet-Engine Compressor I - Over-All Performance Characteristics at Equivalent Impeller Speeds from 6000 to 13,400 RPM (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The NACA is investigating a series of J-33 turbojet-engine compressors to determine the over-all and component performances and to improve theories of flow through large centrifugal compressors, The production model J-33-A-21 was operated over a range of inlet temperatures from 80 to -40 F and inlet pressures from 14 to 5 inches mercury absolute for equivalent impeller speeds from 6000 to 13,400 rpm. At the equivalent design speed of 11,500 rpm, the compressor had a peak pressure ratio of 3.98 at an equivalent weight flow of 73.4 pounds per second and an adiabatic temperature-rise , efficiency of 0.701. When the compressor speed was reduced from the design speed to 6000 rpm, the adiabatic temperature-rise efficiency increased to 0.747. At the maximum equivalent speed investigated (13,400 rpm), a peak pressure ratio of 5.09 was obtained at an adiabatic temperature-rise efficiency of 0.617 and an equivalent weight flow of 66.O pounds per second. An increase in inlet pressure from 5.5 to 14 inches mercury absolute, with a consequent increase in Reynolds number index, improved the pressure ratio but had no apparent effect on the ratio of temperature rise through the compressor to inlet temperature. The variation of the peak adiabatic temperature-rise efficiency with inlet pressure is in the direction that would be expected from a Reynolds number effect. Decrease in the inlet temperature from 80 to -40 F, with a consequent increase in Reynolds number index, resulted in scatter of the pressure-ratio data and increased values of temperature ratio. The variation of the adiabatic temperature-rise efficiency with inlet temperature is probably the result of heat-transfer effects and scatter in the pressure ratio.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SE8C15
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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    Preliminary Results of an Altitude-Wind-Tunnel Investigation of an Axial-Flow Gas Turbine-Propeller Engine (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: As part of an investigation of the performance and operational characteristics of the axial-flow gas turbine-propeller engine, conducted in the Cleveland altitude wind tunnel, the performance characteristics of the compressor and the turbine were obtained. The data presented were obtained at a compressor-inlet ram-pressure ratio of 1.00 for altitudes from 5000 to 35,000 feet, engine speeds from 8000 to 13,000 rpm, and turbine-inlet temperatures from 1400 to 2100 R. The highest compressor pressure ratio obtained was 6.15 at a corrected air flow of 23.7 pounds per second and a corrected turbine-inlet temperature of 2475 R. Peak adiabatic compressor efficiencies of about 77 percent were obtained near the value of corrected air flow corresponding to a corrected engine speed of 13,000 rpm. This maximum efficiency may be somewhat low, however, because of dirt accumulations on the compressor blades. A maximum adiabatic turbine efficiency of 81.5 percent was obtained at rated engine speed for all altitudes and turbine-inlet temperatures investigated.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E8F10c
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 58
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    Compressive Strength of Tapered Airplane Struts (1923)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Methods are here given for ascertaining the value of n in Euler's simplified formula, P = n (EI/l(sup 2)), for the compressive strength of tapered airplane struts, by estimating from curves and by calculation.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-171
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 59
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    Test Report on Three- and Six-Component Measurements on a Series of Tapered Wings of Small Aspect Ratio (1948)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The investigations of the reports to 4 on wings of small aspect ratio are continued. The present report deals with the results of the three- and six-component measurements and the flow pictures of the triangular wing series with the aspect ratio Lambda = 3 to Lambda = 1.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1176 , Untersuchungen und Mitteilungen; 1023/5
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 60
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    [Neue Nr. 5519] Hungen / Geologische Karte (1921)
    Hessisches Landesamt für Bodenforschung, Wiesbaden
    In:  SUB Göttingen | KART B 104:5519 | KART H 86:5519
    Details
    Publication Date: 2022-11-22
    Description: Geologische Karte 1: 25 000 mit Erläuterungen. Digitalisat des FID GEO (Fachinformationsdienst Geowissenschaften der festen Erde), erstellt durch das GDZ (Göttinger Digitalisierungszentrum), Karte aus dem Bestand der SUB Göttingen.
    Description: map
    Description: DFG, SUB Göttingen
    Keywords: ddc:912 ; ddc:554.3 ; ddc:943.2 ; Geologische Karte ; Hungen
    Language: German
    Type: doc-type:carthographicMaterial
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    CITATION GEO-LEO
  • 61
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    [Neue Nr. 5420] Schotten / Geologische Karte (1924)
    Staatsverlag, Darmstadt
    In:  SUB Göttingen | KART B 104:5420 | KART H 86:5420
    Details
    Publication Date: 2022-11-22
    Description: Geologische Karte 1: 25 000 mit Erläuterungen. Digitalisat des FID GEO (Fachinformationsdienst Geowissenschaften), erstellt durch das GDZ (Göttinger Digitalisierungszentrum), Karte aus dem Bestand der SUB Göttingen.
    Description: DFG, SUB Göttingen
    Description: map
    Description: DFG, SUB Göttingen
    Keywords: ddc:912 ; ddc:943.2 ; ddc:554.3 ; Schotten ; Geologische Karte
    Language: German
    Type: doc-type:carthographicMaterial
    Format: 134
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    CITATION GEO-LEO
  • 62
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    [Neue Nr. 6118] Roßdorf / Geologische Karte (1938)
    Hessische Geologische Landesanstalt, Darmstadt
    In:  SUB Göttingen | KART B 104:6118 | KART H 86:6118
    Details
    Publication Date: 2022-11-22
    Description: Geologische Karte 1: 25 000 mit Erläuterungen. Digitalisat des FID GEO (Fachinformationsdienst Geowissenschaften), erstellt durch das GDZ (Göttinger Digitalisierungszentrum), Karte aus dem Bestand der SUB Göttingen.
    Description: map
    Description: DFG, SUB Göttingen
    Keywords: ddc:912 ; ddc:554.3 ; Roßdorf ; Geologische Karte
    Language: German
    Type: doc-type:carthographicMaterial
    Format: 122
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    CITATION GEO-LEO
  • 63
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    [Neue Nr. 5520] Nidda / Geologische Karte (1924)
    Hessisches Landesamt für Bodenforschung, Wiesbaden
    In:  SUB Göttingen | KART B 104:5520 | KART H 86:5420
    Details
    Publication Date: 2022-11-22
    Description: Geologische Karte 1: 25 000. Digitalisat des FID GEO (Fachinformationsdienst Geowissenschaften), erstellt durch das GDZ (Göttinger Digitalisierungszentrum), Karte aus dem Bestand der SUB Göttingen. Koordinaten Vorlage: E 009 00 - E 009 10 /N 050 30 - N 050 24.
    Description: map
    Description: DFG, SUB Göttingen
    Keywords: ddc:912 ; ddc:554.3 ; Geologische Karte ; Nidda
    Language: German
    Type: doc-type:carthographicMaterial
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    CITATION GEO-LEO
  • 64
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    [Neue Nr. 1860] Degow [Dygowo] / Geologische Karte (1921)
    Kraatz, Berlin
    In:  SUB Göttingen | KART B 140:1860 | KART H 140:Degow
    Details
    Publication Date: 2024-02-21
    Description: Geologische Karte 1: 25 000 mit Erläuterungen. Digitalisat des FID GEO (Fachinformationsdienst Geowissenschaften), erstellt durch das GDZ (Göttinger Digitalisierungszentrum), Karte aus dem Bestand der SUB Göttingen. Koordinaten Vorlage: Nullmeridian Ferro E 033 20 - 033 30 / N 054 12 - 054 06.
    Description: map
    Description: DFG, SUB Göttingen
    Keywords: ddc:912 ; ddc:554.3 ; Geologische Karte
    Language: German
    Type: doc-type:carthographicMaterial
    Format: 38
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    CITATION GEO-LEO
  • 65
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    [Neue Nr. 1760] Lassehne [Łasin Koszaliński] / Geologische Karte (1921)
    Kraatz, Berlin
    In:  SUB Göttingen | KART B 140:1760 | KART H 140:Lassehne
    Details
    Publication Date: 2024-02-21
    Description: Geologische Karte 1: 25 000 mit Erläuterungen. Digitalisat des FID GEO (Fachinformationsdienst Geowissenschaften), erstellt durch das GDZ (Göttinger Digitalisierungszentrum), Karte aus dem Bestand der SUB Göttingen. Koordinaten Vorlage: Nullmeridian Ferro E 033 20 - 033 30 / N 054 18 - 054 12.
    Description: map
    Description: DFG, SUB Göttingen
    Keywords: ddc:912 ; ddc:554.3 ; Geologische Karte
    Language: German
    Type: doc-type:carthographicMaterial
    Format: 38
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    CITATION GEO-LEO
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    [Neue Nr. 1289] Königsberg (Ost) [Kaliningrad, Калинингра́д] / Geologische Karte (1916)
    Kraatz, Berlin
    In:  SUB Göttingen | KART B 140:1289 | KART H 140:Königsberg-Ost
    Details
    Publication Date: 2024-05-23
    Description: Geologische Karte 1: 25 000 mit Erläuterungen. Digitalisat des FID GEO (Fachinformationsdienst Geowissenschaften), erstellt durch das GDZ (Göttinger Digitalisierungszentrum), Karte aus dem Bestand der SUB Göttingen. Koordinaten Vorlage: Nullmeridian Ferro E 038 10 – 038 20 / N 054 42 - 054 48.
    Description: map
    Description: DFG, SUB Göttingen
    Keywords: ddc:912 ; ddc:554.3 ; Geologische Karte
    Language: German
    Type: doc-type:carthographicMaterial
    Format: 78
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    CITATION GEO-LEO
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