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  • Other Sources  (347)
  • 2005-2009
  • 1980-1984
  • 1935-1939
  • 1930-1934  (347)
  • 1932  (162)
  • 1931  (185)
  • 1
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    Microseisms in North-America (1931)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 21, no. 3, pp. 1-24, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1931
    Keywords: Micro seismicity ; Seismology ; NOISE ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    Structure and temperature of the stratosphere (1931)
    In:  Bull. Am. Meteor. Soc., Milano, Gustav Fischer, vol. 12, no. 3, pp. 207, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1931
    Keywords: Geothermics ; Meteorology ; Earth model, also for more shallow analyses !
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    Is present tilting in North America due to glacial melting (1932)
    In:  Pan Am. Geologist, Milano, Gustav Fischer, vol. 58, no. 3, pp. 67-68, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1932
    Keywords: Tectonics ; Inelastic
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    Experiments testing seismographic methods for determining crustal structure (1932)
    In:  Pan Am. Geologist, Milano, Gustav Fischer, vol. 58, no. 3, pp. 65-66, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1932
    Keywords: Seismometer ; CRUST ; Earth model, also for more shallow analyses ! ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    Travel time curves at small distances and wave velocities in Southern California (1932)
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 35, no. 3, pp. 6-45, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1932
    Keywords: Travel time ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 6
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    On the transmission of seismic waves on the bottom surface of an ocean (1931)
    In:  Bull. Earthq. Res. Inst. Univ. Tokyo, Luxembourg, Deutsche Geophys. Gesellschaft, vol. 9, no. 3, pp. 115, pp. 8045, (ISSN: 1340-4202)
    Details
    Publication Date: 1931
    Keywords: Waves ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 7
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    Berichtigungen und Ergänzungen zu Band 4 (1932)
    Bornträger
    In:  Professional Paper, Handbuch der Geophysik, Volume 4: Erdbeben (finished), 12+ 1202 S., Berlin, Bornträger, vol. 3, no. VIIa, pp. 1186-1190, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1932
    Keywords: Seismology ; Earthquake
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    BIBLIOGRAPHY SEISMOLOGY
  • 8
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    Der Aufbau der Atmosphäre (1932)
    Bornträger
    In:  Professional Paper, Handbuch der Geophysik, Volume 9: Physik der Atmosphäre 2 (only 1., 2., and 3. part), 8 + 698 S., Berlin, Bornträger, vol. 3, no. VIIa, pp. 1-88, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1932
    Keywords: Meteorology
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    BIBLIOGRAPHY SEISMOLOGY
  • 9
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    Structure of the earth's crust as derived from seismograms (1931)
    In:  Pan Am. Geologist, Milano, Gustav Fischer, vol. 55, no. 3, pp. 373-374, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1931
    Keywords: Earth model, also for more shallow analyses ! ; Seismology ; Seismics (controlled source seismology)
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    BIBLIOGRAPHY SEISMOLOGY
  • 10
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    Pseudoseisms caused by abnormal audibility of gunfire in California (1931)
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 31, no. 3, pp. 155-157, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1931
    Keywords: Seismicity ; Seismology ; Nuclear explosion ; NOISE
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    BIBLIOGRAPHY SEISMOLOGY
  • 11
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    Mit welcher Genauigkeit läßt sich die Schallgeschwindigkeit in der Stratosphäre finden? (1932)
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 35, no. 3, pp. 46-50, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1932
    Keywords: Velocity analysis ; Meteorology ; Acoustics
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    BIBLIOGRAPHY SEISMOLOGY
  • 12
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    Structure of the earth's crust derived from seismograms (1932)
    In:  Bull. Geol. Soc. Am., Milano, Gustav Fischer, vol. 43, no. 3, pp. 236-237, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1932
    Keywords: CRUST ; Seismology ; Seismics (controlled source seismology)
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    BIBLIOGRAPHY SEISMOLOGY
  • 13
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    The earthquake in Santa Monica Bay, California, on August 30, 1930 (1932)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 22, no. 3, pp. 138-154, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1932
    Keywords: Seismology ; Earthquake ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 14
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    Experiments testing seismographic methods for determining crustal structure (1932)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 22, no. 3, pp. 185-246, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1932
    Keywords: Seismometer ; CRUST ; Earth model, also for more shallow analyses ! ; Seismology ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 15
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    Aufbau und Temperatur der Stratosphäre (1931)
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 32, no. 3, pp. 87-94, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1931
    Keywords: Geothermics ; Earth model, also for more shallow analyses ! ; Meteorology
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    BIBLIOGRAPHY SEISMOLOGY
  • 16
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    On supposed discontinuities in the mantle of the earth (1931)
    In:  Bull. Seism. Soc. Am., Milano, Gustav Fischer, vol. 21, no. 3, pp. 216-223, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1931
    Keywords: earth mantle ; Earth model, also for more shallow analyses ! ; Seismology ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 17
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    Der physikalische Aufbau der Erde (1931)
    Bornträger
    In:  Professional Paper, Handbuch der Geophysik, Volume 2: Der Aufbau der Erde (finished), 15 + 1119 S., Berlin, Bornträger, vol. 3, no. VIIa, pp. 440-564, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1931
    Keywords: Earth model, also for more shallow analyses ! ; Seismology ; Review article
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  • 18
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    Die forstlich wichtigsten Klimazahlen von Deutschland (1931)
    In:  Hannover, Schaper
    Details
    Publication Date: 1931
    Description: Karten zur räumlichen Verteilung forstlich wichtiger Parameterr (Niederschlag, Temperatur, Spätfrosttage etc.) in Deutschland KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
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  • 19
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    Die Abhängigkeit der Erträge vom Wetter (1931)
    In:  Landwirtschaft. Wochenschrift für die Provinz Sachsen, Heft 48
    Details
    Publication Date: 1931
    Keywords: Sachsen
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  • 20
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    Untersuchungen über die Ernteschwankungen der Kartoffeln (1931)
    In:  Dissertation, Berlin.
    Details
    Publication Date: 1931
    Description: Beschreibung der Ernteschwankungen im Zusammenhang zu Witterungsfaktoren,eher allgemeiner,der Fokus der Arbeit liegt auf wirtschaftlicher Bedeutung, hier besonders die Preisgestaltung durch die Ertragsschwankungen KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland, regional aufgelöst ; 1893-1929 ; Kartoffeln ; Ertrag ; Getreide ; Landwirtschaft ; Witterung
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  • 21
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    The influence of weather on crops: 1900-1930 (1931)
    In:  In U. S. Department of Agriculture, (ed.) A Selected and Annotated Bibliography, Washington.
    Details
    Publication Date: 1931
    Description: Kompendium zum Zusammenhang Wetter und Pflanzen, landwirtschaftlich, gärtnerische und forstwirtschaftliche Kulturen, Schädlinge und Gesundheit, 2324 Literaturstellen mit kurzer Zusammenfassung KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: weltweit ; 1650-1930 ; Insekten ; Umweltmedizin ; Zuckerrüben ; Kartoffeln ; Anbautermine ; Infektionskrankheiten ; Boden ; Botanik ; Buche ; Eiche ; Ertrag ; Fichte ; Forst ; Getreide ; Hafer ; Kiefer ; Klima ; Korrelationsmethode ; Landwirtschaft ; Mais ; Niederschlag ; Pflanzenkrankheit ; Pflanzenschädling ; Phänologie ; Rangordnungsmethode ; Roggen ; Roterle ; Temperatur ; Trockenheit ; Vegetationsperiode ; Verdunstung ; Wachstum ; Waldbrand ; Waldwachstum ; Wassermangel ; Weizen ; Wetterbeobachtung ; Wind ; Witterung ; Witterungsextreme ; Düngung ; Globalstrahlung ; Hackfrüchte ; Erbsen ; Wein
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  • 22
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    Klima und Boden in ihrer Wirkung auf das Pflanzenleben (1931)
    In:  Edward Arnold & Co., London.
    Details
    Publication Date: 1931
    Description: Allgemeine Zusammenhänge Klima und Pflanzenwachstum KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland ; Boden ; Klima ; Landwirtschaft ; Wachstum
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  • 23
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    Einfluß der Witterung auf Wachstum un Ertrag von 13 Pferdebohnensorten (1931)
    In:  Wiss. Archiv für Landw. A 6, 465-524
    Details
    Publication Date: 1931
    Description: Einfluß des Niederschlags, der Temperatur und Sonnenscheindauer auf Länge der Vegetationszeit, Korn- und Strohertrag bei Pferdebohnen unterschiedlicher Reifegruppen mithilfe des Rangordnungsverfahren KATASTER-BESCHREIBUNG: Zusammenfassung der Sorten nach Blühbeginn in 3 Gruppen, auf dem Versuchsstandort schwerer Boden und hoher Niederschlag (668mm), positiver Einfluss von Temperatur und Sonnenscheindauer auf den Ertrag, Bestimmung von kritischen Perioden KATASTER-DETAIL: Delta Nied+ (Auflaufen), dann Kornertrag+; Delta Nied+, dann Kornertrag -; Delta Temp+, dann Kornertrag -: Delta Sonn+(Auflaufen, bis Blühbeginn, bis Abreife), dann Kornertrag+;
    Keywords: Bayern ; 1921-1928 ; Ertrag ; Niederschlag ; Rangordnungsmethode ; Temperatur ; Sonnenscheindauer
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  • 24
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    Die Häufigkeit nasser und dürrer Sommermonate in Mitteldeutschland (1931)
    In:  Der Kulturtechniker 34:30-60
    Details
    Publication Date: 1931
    Keywords: Mitteldeutschland ; 1900-1930
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  • 25
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    Waldbau. Wesentliche Eigenschaften der Holzarten. Teil 2 (1931)
    Details
    Publication Date: 1931
    Description: genaue Beschreibung der Methode zu den Klimaansprüchen der Baumarten und der abgeleiteten Klimazahlen von Hackmann (1931) KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
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  • 26
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    Betrachtung über Ertrag und Qualität des Hafers in ihrer Abhängigkeit von Sorte und Jahreswitterung. (1931)
    In:  Zeitschr. Pflanzenbau 8:285.
    Details
    Publication Date: 1931
    Description: Auswertung von 6-jährigen Sortenversuchen der Landeszuchtanstalt Weihenstephan, Beziehungen von Temperatur und Niederschlag in Dekaden zum Ertrag und der Qualität von verschiedenen Hafersorten KATASTER-BESCHREIBUNG: Einfluss der Witterung auf den Ertrag von Hafer KATASTER-DETAIL: Delta Nied (Keimzeit) +, dann Keimzeit +; Delta T (Keimzeit) -, dann Keimzeit +; Delta T (Bestockungsperiode) +, dann Ertrag -;
    Keywords: Bayern ; 1926-31 ; Ertrag ; Hafer ; Niederschlag ; Temperatur ; Witterung
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  • 27
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    Handbuch der Geophysik, Volume 6: Geophysikalische Aufschlußmethoden (only 1. part), 5 + 312 S. (1931)
    Bornträger
    In:  Berlin, Bornträger, vol. 12, 189 S., no. Subvol. b, pp. 220, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1931
    Keywords: Applied geophysics
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    BIBLIOGRAPHY SEISMOLOGY
  • 28
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    Einleitung: Allgemeines über Geophysik (1931)
    Bornträger
    In:  Professional Paper, Handbuch der Geophysik, Volume 1: Die Erde als Planet (finished), 15 + 970 S., Berlin, Bornträger, vol. 3, no. VIIa, pp. 1-7, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1931
    Keywords: Review article ; Planetology
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  • 29
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    Abkühlung und Temperatur der Erde (1931)
    Bornträger
    In:  Professional Paper, Handbuch der Geophysik, Volume 2: Der Aufbau der Erde (finished), 15 + 1119 S., Berlin, Bornträger, vol. 3, no. VIIa, pp. 1-38, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1931
    Keywords: Review article ; Planetology ; Geothermics
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    BIBLIOGRAPHY SEISMOLOGY
  • 30
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    Die Schallausbreitung in der Atmosphäre (1932)
    Bornträger
    In:  Professional Paper, Handbuch der Geophysik, Volume 9: Physik der Atmosphäre 2 (only 1., 2., and 3. part), 8 + 698 S., Berlin, Bornträger, vol. 3, no. VIIa, pp. 89-145, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1932
    Keywords: Meteorology ; Wave propagation ; Acoustics
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    BIBLIOGRAPHY SEISMOLOGY
  • 31
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    The command system malfunction of the telstar satellite (1932)
    In:  CASI
    Details
    Publication Date: 2006-10-26
    Description: Command system malfunction of telstar satellite due to transistor surface damage in redundant command decoder
    Keywords: COMPUTERS
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    NASA TECHNICAL REPORTS
  • 32
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    Test of NACA 21 Airfoil (Modified NACA M-6) Including Characteristics at Positive and Negative Angles of Attack (1932)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance; Research and Support Facilities (Air); Aerodynamics
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  • 33
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    Counter-propeller (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A counter-propeller is a fixed propeller smaller than the main propeller, mounted either fore or aft of the latter and performing the function of changing the direction of motion of the fluid filaments, which naturally tend to adopt a helicoidal form. This paper presents a consideration of the real advantage of counter-propellers on aircraft and the best shape of the blades. First, the author determines the possible energy absorption by the tangential increments. This process will be facilitated by the examination of the polygons of the relative velocities fore and aft of the generic section, of radius r, of one of the blades of the propeller.
    Type: NACA-TM-587
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  • 34
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    Clerget 100 hp heavy-oil engine (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A complete technical description of the Clerget heavy-oil engine is presented along with the general characteristics. The general characteristics are: 9 cylinders, bore 120 mm, stroke 130 mm, four-stroke cycle engine, rated power limited to 100 hp at 1800 rpm; weight 228 kg; propeller with direct drive and air cooling. Moving parts, engine block, and lubrication are all presented.
    Type: NACA-TM-603
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  • 35
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    The aerodynamic wind vane and the inherent stability of airplanes (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The design of the wind vane described rests on the following line of reasoning: An airplane, originally in equilibrium about its C.G. is assumed to be deflected from this position through an angle (delta)i, the variation (delta)i being so sudden that the path of the C.G. and the airplane speed do not change while it is taking place. The aerodynamic forces acting on the wings, tail surfaces, fuselage, etc., which, as a whole, exerted a zero moment (M(sub G) = 0) about the center of gravity at the instant of equilibrium, now exert a moment M(sub G) not equal to 0.
    Type: NACA-TM-607
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  • 36
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    Aeronautical education and research at the Swiss Institute of Technology in Zurich (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Progress in the scientific and practical fields of aviation has caused the Swiss Institute of Technology to organize lectures and practical training courses in all three branches of aeronautics and to found centers of scientific research, laboratories, etc., in order to supply the government and industries with scientifically and technically trained engineers.
    Type: NACA-TM-616
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  • 37
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    Landing of seaplanes (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report begins with a brief resume of a theoretical consideration and its results. Then a description is presented of the processes at the moment a keeled bottom strikes the water and the formulas and solutions are given. Lastly a discussion of the application of these results to practical problems is given.
    Type: NACA-TM-622
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  • 38
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    Experiments with a wing from which the boundary layer is removed by suction (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of the first investigation of the physical principle of preventing the streamline separation by removing the boundary layer. It was aeronautical, in that it dealt with airfoils, but the results are of a very general application.
    Type: NACA-TM-634
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  • 39
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    The dangerous sideslip of a stalled airplane and its prevention (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation covers only that phase of airplane accidents which are the result of sideslip. We examine the circumstances under which this occurs, study the behavior of present-day airplane types (monoplane, conventional and staggered biplane) therein and endeavor to find a solution whereby this danger may be avoided.
    Type: NACA-TM-638
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  • 40
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    Spatial buckling of various types of airplane strut systems (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Equations are presented for two and three dimensional strut systems along with tables of equations.
    Type: NACA-TM-647
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    NASA TECHNICAL REPORTS
  • 41
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    Lift distribution and longitudinal stability of an airplane (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The preliminary calculation of the airplane polar and hence of the flight performances and characteristics rests on the assumption of an elliptical lift distribution at all altitudes. For large angles of attack below C(sub a (sub max)), this method of calculation yields no satisfactory agreement with measurements made in flight. An attempt is made to eliminate the errors in the preliminary calculation by the assumption of a disturbance of the lift distribution in this angle-of-attack range, which is so important for the constructor. An explanation is also given of the great differences found in flight with and without propeller slipstream.
    Type: NACA-TM-641
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  • 42
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    The German Investigation of the Accident at Meopham (England) (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is a recounting of the German investigation of the crash of a commercial Junkers F 13 ge in England. The English report is examined and compared with the German interpretation of the accident.
    Type: NACA-TM-669
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  • 43
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    Measurements of vertical air currents in the atmosphere (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: To summarize, the experiments with balloons, sailplanes and light airplanes conducted thus far, reveal the vertical velocities of the air to be primarily dependent on the vertical temperature distribution. Stable stratifications result in up-and-down currents forced by the contour of the ground, which are readily recognized in flight and, if need be, may be avoided.
    Type: NACA-TM-648
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  • 44
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    Development of tailless and all-wing gliders and airplanes (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tailless airplanes are characterized by having all their control surfaces, especially the elevator, incorporated in the wings. This paper provides a discussion of the history of their development and current state of development.
    Type: NACA-TM-666
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  • 45
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    Twelfth Rhon soaring contest, 1931 (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The crew of the "Fafnir" was given an excellent opportunity for collecting first-hand data as to the usefulness of gliders in the Alps. It is necessary to recount the remarkable glider achievements ahead of the Rhon Soaring Contest, in order to understand the tension and expectation with which the Rhon contest was anticipated.
    Type: NACA-TM-671
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  • 46
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    Towing tests of models as an aid in the design of seaplanes (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report concerns the making and evaluation of a towing test of a seaplane float system. Some of the topics considered are: 1) the influence of the wing cell and power plant on the take-off performance; 2) the determination of the resistance curve for the take-off free to trim; 3) the resistance curves with elevator control (at fixed trims); 4) take-off time and take-off run.
    Type: NACA-TM-676 , Gesellschaft der Freunde und Forderer der Hamburgischen Schiffbau-Versuchsanstalt (9th : June 11, 1930)
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  • 47
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    Airplane stability in taxying (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The stability analysis of an airplane while rolling is much more simplified to the extent that it can be obtained for numerical data which can be put to practical use in the design of landing gear dimensions. Every landing gear type attains to a critical ground friction coefficient that decides the beginning of instability, i.e., nosing over. This study has, in addition, a certain interest for the use of wheel brakes.
    Type: NACA-TM-682
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  • 48
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    Speed and pressure recording in three-dimensional flow (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Van der Megge Zijnen's spherical Pitot tube with its 5 test holes insures a simultaneous record of static pressure and magnitude and direction of velocity in three-dimensional flow. The report treats the method as well as the range of application of this Pitot in the light of modern knowledge on flow around spheres.
    Type: NACA-TM-688
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  • 49
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    The Problem of Tire Sizes for Airplane Wheels (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: On the basis of experiments and theoretical considerations a proposal is made for a standard tire series for airplane wheels, without regard to existing standards.
    Type: NACA-TM-689
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  • 50
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    A study of curvilinear flight (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: When an airplane describes a curve it takes a certain time for it to turn from level to inclined position and then back to level again. In the following, we express the motion about the horizontal axis as "roll" or "bank" and the motion perpendicular to the vertical axis, i.e., the actual curve, as "turn." Equations and tables provide results on various aspects of turns, control settings, acceleration, inertia moments, and angular velocity.
    Type: NACA-TM-615
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  • 51
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    Mechanical similitude and turbulence (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report deals with the theory of the vortex street which enables the reproduction of the mechanism of the form resistance with suitable approximation under stated conditions, although such a resistance is precluded in a fluid which is perfectly inviscid. Disregarding for the present the origination of the vortex, the stream attitude in the wake of the body may be described approximately correct by the representation of individual vortices, without transgressing the law governing the motion of such vortices in an ideal fluid. Another striking example is the theory of the induced drag of wings, which likewise shows the extent of applying the vortex equations without overstepping the bounds of the dynamics of ideal fluids.
    Type: NACA-TM-611
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  • 52
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    Determination of resistance and trimming moment of planing water craft (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents a new theory which makes it possible to interpret the resistance and the trimming moment for any loading of a planing aircraft when these values are given for one load. This application of the new theory forms the basis of the present paper. Derivations of various conversion formulas are given as well as numerous examples.
    Type: NACA-TM-619
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  • 53
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    The new "Charlestop" remote brake transmission and control (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents a description, diagrams and photographs of the Charlestop remote brake system.
    Type: NACA-TM-640
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  • 54
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    Load assumptions for the landing impact of seaplanes (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The formula for the impact of floats must include the enlargement factor itself as well as the type of enlargement. The latter is preferably characterized by the change in surface loading. It is shown that the enlargement of a small seaplane generally results in a changed float (or boat) loading as well as wing loading. The conditions of starting stipulate the retention of the float loading when changing from single-float (boat) to twin-float arrangement. This contingency is followed by an increased impact factor in the twin-float type against the otherwise equivalent single-float type.
    Type: NACA-TM-643
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  • 55
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    Relations between ship design and seaplane design (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report examines various aspects of seaplane construction; namely, stability, propulsion, water-tight bulkheads, fire protection, and construction.
    Type: NACA-TM-645
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  • 56
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    Combustion Velocity of Benzine-Benzol-Air Mixtures in High-Speed Internal-Combustion Engines (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The present paper describes a device whereby rapid flame movement within an internal-combustion engine cylinder may be recorded and determined. By the aid of a simple cylindrical contact and an oscillograph the rate of combustion within the cylinder of an airplane engine during its normal operation may be measured for gas intake velocities of from 30 to 35 m/s and for velocities within the cylinder of from 20 to 25 m/s. With it the influence of mixture ratios, of turbulence, of compression ratio and kind of fuel on combustion velocity may be determined. Besides the determination of the influence of the above factors on combustion velocity, the degree of turbulence may also be determined. As a unit of reference in estimating the degree of turbulence, the intake velocity of the charge is chosen.
    Type: NACA-TM-668
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  • 57
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    Vertical descent of the autogiro (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The purpose of this report is to show that only part of the system of rotating blades really is in the "windmill decelerating attitude" when the profile drag is sufficiently low. This particular part receives more torque from the air loads than can be absorbed by the profile drag. As a result thereof the rotating autogiro blade, when its torque is zero, is in part a propeller which functions in the "annular vortex attitude."
    Type: NACA-TM-673
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  • 58
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    Stresses developed in seaplanes while taking off and landing (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In the case of seaplanes, the lack of elastic shock absorbers, the presence of which might be quite dangerous, especially in taking off, makes it necessary to give some consideration to the phenomenon of landing. Special consideration must be given the process of taking off, since even moderately rough water may develop rather large stresses. The purpose of this communication is to show what has been accomplished in Italy and other countries and to draw a few useful conclusions.
    Type: NACA-TM-677 , Societa Italiana per il Progresso delle Scienze (20th : 1931 : Milan, Italy)
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  • 59
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    The Aerodynamic Characteristics of a Slotted Clark Y Wing as Affected by the Auxiliary Airfoil Position (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Aerodynamic force tests on a slotted Clark Y wing were conducted in a vertical wind tunnel to determine the best position for a given auxiliary airfoil with respect to the main wing. A systematic series of 100 changes in location of the auxiliary airfoil were made to cover all the probable useful ranges of slot gap, slot width, and slot depth. The results of the investigation may be applied to the design of automatic or controlled slots on wings with geometric characteristics similar to the wing tested. The best positions of the auxiliary airfoil were covered by the range of the tests, and the position for desired aerodynamic characteristics may easily be obtained from charts prepared especially for the purpose.
    Type: NACA-TR-400
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  • 60
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    Flame Movement and Pressure Development in an Engine Cylinder (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation describes a visual method for making stroboscopic observations, through a large number of small windows, of the spread of flame throughout the combustion chamber of a gasoline engine. Data, secured by this method on a small engine burning gaseous fuels, are given to show the effects of mixture ratio, spark advance, engine speed, charge density, degree of dilution, compression ratio, and fuel composition on flame movement in the cylinder. Partial indicator diagrams showing pressure development during the combustion period are included. Although present knowledge is not sufficient to permit qualitative evaluation of the separate effects on flame movement of chemical reaction velocity, thermal expansion of burned gases, resonance, turbulence, and piston movement, the qualitative influence of certain of these factors on some of the diagrams is indicated.
    Type: NACA-TR-399
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  • 61
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    Investigation of Damping Liquids for Aircraft Instruments : II (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Data are presented on the kinematic viscosity, in the temperature range -50 degrees to +30 degrees C. of pure liquids and of solutions of animal oils, vegetable oils, mineral oils, glycerine, and ethylene glycol in various low freezing point solvents. It is shown that the thermal coefficient of kinematic viscosity as a function of the kinematic viscosity of the solutions of glycerine and ethylene glycol in alcohols is practically independent of the temperature and the chemical composition of the individual liquids. This is similarly true for the mineral oil group and, for a limited temperature interval, for the pure animal and vegetable oils. The efficiency of naphthol, hydroquinone, and diphenylamine to inhibit the change of viscosity of poppyseed and linseed oils was also investigated.
    Type: NACA-TR-398
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  • 62
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    Full-Scale Tests of Metal Propellers at High Tip Speeds (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes tests of 10 full-scale metal propellers of several thickness ratios at various tip speeds up to 1,350 feet per second. The results indicate no loss of efficiency up to tip speeds of approximately 1,000 feet per second. Above this tip speed the loss is at a rate of about 10 per cent per 100 feet per second increase relative to the efficiency at the lower speeds for propellers of pitch diameter ratios 0.3 to 0.4. Propellers having sections of small thickness ratio can be run at slightly higher speeds than thick ones before beginning to lose efficiency.
    Type: NACA-TR-375
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  • 63
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    Present status of aircraft instruments (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report gives a brief description of the present state of development and of the performance characteristics of instruments included in the following group: speed instruments, altitude instruments, navigation instruments, power-plant instruments, oxygen instruments, instruments for aerial photography, fog-flying instruments, general problems, summary of instrument and research problems. The items considered under performance include sensitivity, scale errors, effects of temperature and pressure, effects of acceleration and vibration, time lag, damping, leaks, elastic defects, and friction.
    Type: NACA-TR-371
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  • 64
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    A new chart for estimating the absolute ceiling of an airplane (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is concerned with the derivation of a chart for estimating the absolute ceiling of an airplane. This chart may be used in conjunction with the usual curves of power required and power available as an accurate substitute for extended calculation, or it may be used in the estimation of absolute ceiling when power curves are not available.
    Type: NACA-TR-368
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  • 65
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    Maneuverability Investigation of the F6C-3 Airplane with Special Flight Instruments (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation was made for the purpose of obtaining information on the maneuverability of the F6C-3 airplane. It is the first of a series of similar investigations to be conducted on a number of military airplanes for the purpose of comparing the abilities of these airplanes to maneuver, and also to establish a fund of quantitative data which may be used in formulating standards of comparison for rating the maneuverability of any airplane. A large part of this initial investigation was necessarily devoted to the development and trial of methods suitable for use in subsequent investigations of this nature. Air speed, angular velocity, linear acceleration, and position of the control surfaces were measured by instruments in the airplane during loops, push-downs, pull-outs from dives, pull-ups from level flight, barrel rolls, and spins. The coordinates of flight paths were deduced from the data whenever possible, and were checked in some cases by the use of a camera obscura. The results are given in curves showing the variation of the measured quantities with respect to time, and maximum values are tabulated.
    Type: NACA-TR-369
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  • 66
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    Annual report of the National Advisory Committee for Aeronautics (17th).administrative report including Technical Report nos. 365 to 400 (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the president, congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
    Type: NACA-AR-17
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  • 67
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    The Pressure Distribution over the Wings and Tail Surfaces of a PW-9 Pursuit Airplane in Flight (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of an investigation to determine (1) the magnitude and distribution of aerodynamic loads over the wings and tail surfaces of a pursuit-type airplane in the maneuvers likely to impose critical loads on the various subassemblies of the airplane structure. (2) To study the phenomenon of center of pressure movement and normal force coefficient variation in accelerated flight, and (3) to measure the normal accelerations at the center of gravity, wing-tip, and tail, in order to determine the nature of the inertia forces acting simultaneously with the critical aerodynamic loads. The results obtained throw light on a number of important questions involving structural design. Some of the more interesting results are discussed in some detail, but in general the report is for the purpose of making this collection of airplane-load data obtained in flight available to those interested in airplane structures.
    Type: NACA-TR-364
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  • 68
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    Pressure Fluctuations in a Common-Rail Fuel Injection System (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of an investigation to determine experimentally the instantaneous pressures at the discharge orifice of a common-rail fuel injection system in which the timing valve and cut-off valve were at some distance from the automatic fuel injection valve, and also to determine the methods by which the pressure fluctuations could be controlled. The results show that pressure wave phenomena occur between the high-pressure reservoir and the discharge orifice, but that these pressure waves can be controlled so as to be advantageous to the injection of the fuel. The results also give data applicable to the design of such an injection system for a high-speed compression-ignition engine.
    Type: NACA-TR-363
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  • 69
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    Experimental Determination of Jet Boundary Corrections for Airfoil Tests in Four Open Wind Tunnel Jets of Different Shapes (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This experimental investigation was conducted primarily for the purpose of obtaining a method of correcting to free air conditions the results of airfoil force tests in four open wind tunnel jets of different shapes. Tests were also made to determine whether the jet boundaries had any appreciable effect on the pitching moments of a complete airplane model. Satisfactory corrections for the effect of the boundaries of the various jets were obtained for all the airfoils tested, the span of the largest being 0.75 of the jet width. The corrections for angle of attack were, in general, larger than those for drag. The boundaries had no appreciable effect on the pitching moments of either the airfoils or the complete airplane model. Increasing turbulence appeared to increase the minimum drag and maximum lift and to decrease the pitching moment.
    Type: NACA-TR-361
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  • 70
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    Temperature Coefficient of the Modulus of Rigidity of Aircraft Instrument Diaphragm and Spring Materials (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Experimental data are presented on the variation of the modulus of rigidity in the temperature range -20 to +50 degrees C. of a number of metals which are of possible use for elastic elements for aircraft and other instruments. The methods of the torsional pendulum was used to determine the modulus of rigidity and its temperature coefficient for aluminum, duralumin, monel metal, brass, phosphor bronze, coin silver, nickel silver, three high carbon steels, and three alloy steels. It was observed that tensile stress affected the values of the modulus by amounts of 1 per cent or less.
    Type: NACA-TR-358
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  • 71
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    Aircraft accidents : method of analysis (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The revised report includes the chart for the analysis of aircraft accidents, combining consideration of the immediate causes, underlying causes, and results of accidents, as prepared by the special committee, with a number of the definitions clarified. A brief statement of the organization and work of the special committee and of the Committee on Aircraft Accidents; and statistical tables giving a comparison of the types of accidents and causes of accidents in the military services on the one hand and in civil aviation on the other, together with explanations of some of the important differences noted in these tables.
    Type: NACA-TR-357
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  • 72
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    Strength of Rectangular Flat Plates Under Edge Compression (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flat rectangular plates of duralumin, stainless iron, monel metal, and nickel were tested under loads applied at two opposite edges and acting in the plane of the plate. The edges parallel to the direction of loading were supported in V grooves. The plates were all 24 inches long and varied in width from 4 to 24 inches by steps of 4 inches, and in thickness from 0.015 to 0.095 inch by steps of approximately 0.015 inch. There were also a few 1, 2, 3, and 6 inch wide specimens. The loads were applied in the testing machine at the center of a bar which rested along the top of the plate. Load was applied until the plate failed to take any more load. The tests show that the loads carried by the plates generally reached a maximum for the 8 or 12 inch width and that there was relatively small drop in load for the greater widths. Deflection and set measurement perpendicular to the plane of the plate were taken and the form of the buckle determined. The number of buckles were found to correspond in general to that predicted by the theory of buckling of a plate uniformly loaded at two opposite edges and simply supported at the edges.
    Type: NACA-TR-356
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  • 73
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    Airfoil Pressure Distribution Investigation in the Variable Density Wind Tunnel (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of wind tunnel tests of pressure distribution measurements over one section each of six airfoils. Pressure distribution diagrams, as well as the integrated characteristics of the airfoils, are given for both a high and a low dynamic scale or, Reynolds number VL/V, for comparison with flight and other wind-tunnel tests, respectively. It is concluded that the scale effect is very important only at angles of attack near the burble. The distribution of pressure over an airfoil having a Joukowski section is compared with the theoretically derived distribution. A further study of the distribution of pressure over all of the airfoils resulted in the development of an approximate method of predicting the pressure distribution along the chord of any normal airfoil for all attitudes within the working range if the distribution at one attitude is known.
    Type: NACA-TR-353
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  • 74
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    A method of calculating the ultimate strength of continuous beams (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The purpose of this study was to investigate the strength of continuous beams after the elastic limit has been passed. As a result, a method of calculation, which is applicable to maximum load conditions, has been developed. The method is simpler than the methods now in use and it applies properly to conditions where the present methods fail to apply.
    Type: NACA-TR-347
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  • 75
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    Effect of Variation of Chord and Span of Ailerons on Rolling and Yawing Moments at Several Angles of Pitch (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of an extension to higher angles of attack of the investigation of the rolling and yawing moments due to ailerons of various chords and spans on two airfoils having the Clark Y and U. S. A. 27 wings. The measurements were made at various angles of pitch but at zero angle of roll and yaw, the wing chord being set at an angle of +4 degrees to the fuselage axis. In the case of the Clark Y airfoil the measurements have been extended to a pitch angle of 40 degrees, using ailerons of span equal to 67 per cent of the wing semispan and chord equal to 20 and 30 per cent of the wing chord. The work was conducted on wing models of 60-inch span and 10-inch chord.
    Type: NACA-TR-343
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  • 76
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    The drag characteristics of several airships determined by deceleration tests (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of deceleration tests conducted for the purpose of determining the drag characteristics of six airships. The tests were made with airships of various shapes and sizes belonging to the Army, the Navy, and the Goodyear-Zeppelin Corporation. Drag coefficients for the following airships are shown: Army TC-6, TC-10, and TE-2; Navy Los Angeles and ZMC-2; Goodyear Puritan. The coefficients vary from about 0.045 for the small blunt airships to 0.023 for the relatively large slender Los Angeles. This variation may be due to a combination of effects, but the most important of these is probably the effect of length-diameter ratio.
    Type: NACA-TR-397
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  • 77
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    The Effect of Valve Timing Upon the Performance of a Supercharged Engine at Altitude and an Unsupercharged Engine at Sea Level (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation was conducted to determine the comparative effects of valve timing on the performance of an unsupercharged engine at sea level and a supercharged engine at altitude. The tests were conducted on the NACA universal test engine. The timing of the four valve events was varied over a wide range; the engine speeds were varied between 1,050 and 1,500 r.p.m.; the compression ratios were varied between 4.35:1 and 7.35:1. The conditions of exhaust pressure and carburetor pressure of a supercharged engine were simulated for altitudes between 0 and 18,000 feet. The results show that optimum valve timing for a supercharged engine at an altitude of 18,000 feet differs slightly from that for an unsupercharged engine at sea level. A small increase in power is obtained by using the optimum timing for 18,000 feet for altitudes above 5,000 feet. The timing of the intake opening and exhaust closing becomes more critical as the compression ratio is increased.
    Type: NACA-TR-390
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  • 78
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    The Effect of Small Angles of Yaw and Pitch on the Characteristics of Airplane Propellers (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of wind tunnel tests to determine the effect on the characteristics of a propeller of inclining the propeller axis at small angles to the relative wind. Tests were made of a full-scale propeller and fuselage combination at four angles of yaw (0 degree, +5 degrees, +10 degrees, +15 degrees), and of a model propeller, nacelle, and wing combination of five angles of pitch (-5 degrees, 0 degree, +5 degrees, +10 degrees and +15 degrees). The results of the full-scale tests of a propeller and fuselage, without a wing, show that the effect on the propeller performance is small. Similar results are shown by the model test data except that where the propeller is directly in front of the wing there is an appreciable decrease in effective thrust and propulsive efficiency with increase of angle of pitch.
    Type: NACA-TR-389
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  • 79
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    The aerodynamic characteristics of eight very thick airfoils from tests in the variable density wind tunnel (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of wind tunnel tests on a group of eight very thick airfoils having sections of the same thickness as those used near the roots of tapered airfoils. The tests were made to study certain discontinuities in the characteristic curves that have been obtained from previous tests of these airfoils, and to compare the characteristics of the different sections at values of the Reynolds number comparable with those attained in flight. The discontinuities were found to disappear as the Reynolds number was increased. The results obtained from the large-scale airfoil, a symmetrical airfoil having a thickness ratio of 21 per cent, has the best general characteristics.
    Type: NACA-TR-391
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  • 80
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    Comparison of Full-Scale Propellers Having R.A.F.-6 and Clark Y Airfoil Sections (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In this report the efficiencies of two series of propellers having two types of blade sections are compared. Six full-scale propellers were used, three having R. A. F.-6 and three Clark Y airfoil sections with thickness/chord ratios of 0.06, 0.08, and 0.10. The propellers were tested at five pitch setting, which covered the range ordinarily used in practice. The propellers having the Clark Y sections gave the highest peak efficiency at the low pitch settings. At the high pitch settings, the propellers with R. A. F.-6 sections gave about the same maximum efficiency as the Clark Y propellers and were more efficient for the conditions of climb and take-off.
    Type: NACA-TR-378
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  • 81
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    Rolling Moments Due to Rolling and Yaw for Four Wing Models in Rotation (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of a series of autorotation and torque tests on four different rotating wing systems at various rates of roll and at several angles of yaw. The investigation covered an angle of attack range up to 90 degrees and angles of yaw of 0 degree, 5 degrees, 10 degrees, and 20 degrees. The tests were made in a 5-foot, closed-throat atmospheric wind tunnel. The object of the tests was primarily to determine the effects of various angles of yaw on the rolling moments of the rotating wings up to large angles of attack. It was found that at angles of attack above that of maximum lift the rolling moments on the wings due to yaw (or side slip) from 5 degrees to 20 degrees were roughly of the same magnitude as those due to rolling. There was a wide variation in magnitude of the rolling moment due to yaw angle. The rates and ranges of stable autorotation for the monoplane models were considerably increased by yaw, whereas for an unstaggered biplane they were little affected. The immediate cause of the rolling moment due to yaw is apparently the building up of large loads on the forward wing tip and the reduction of loads on the rearward wing tip.
    Type: NACA-TR-379
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  • 82
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    Reduction of turbulence in wind tunnels (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A brief nonmathematical outline is given of modern views as to the nature of the effect of turbulence, and their bearing on the desirability of designing wind tunnels for small or large turbulence. Experiments made on a particular wind tunnel for the purpose of reducing the turbulence are described, to illustrate the influence of certain factors on the magnitude of the turbulence. Moderate changes in the size, shape, and wall thickness of cells of the honeycomb were found to have little effect. The addition of a room honeycomb at the entrance was also of little value in reducing the turbulence. The turbulence decreased with increasing distance between the honeycomb and the measuring station. A further decrease was obtained by using a large area reduction in the entrance cone, with the honeycomb at the extreme entrance end. (author)
    Type: NACA-TR-392
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  • 83
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    The Vertical Wind Tunnel of the National Advisory Committee for Aeronautics (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The vertical open-throat wind tunnel of the National Advisory Committee for Aeronautics is described in this report. The tunnel was built mainly for studying the spinning characteristics of airplane models, but may be used as well for the usual types of wind-tunnel tests. A special spinning balance is being developed to measure the desired forces and moments with the model simulating the spin of an airplane. Satisfactory air flow has been attained with a velocity that is uniform over the jet to within plus or minus 0.5 per cent. The turbulence present in the tunnel has been compared with that of several other tunnels by means of the results of sphere drag tests and was found to average well with the values of those tunnels. Included also in the report are comparisons of results of stable autorotation and of rolling-moment test obtained both in the vertical tunnel and in the old horizontal 5-foot atmospheric tunnel. (author)
    Type: NACA-TR-387
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  • 84
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    The Stieger ST. 4 light airplane (British) : a twin-engine four-seat low-wing cabin monoplane (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-AC-164
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  • 85
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    The Farman night bombers 211 and 212 (French) : four-engine high-wing monoplanes (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-AC-165
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  • 86
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    Supplement to the Supermarine S.6.B. Racing Seaplane (British) : A Low-Wing Twin-Float Monoplane (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-AC-154-Suppl
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  • 87
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    Strength Tests on Thin-walled Duralumin Cylinders in Torsion (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is the first of a series presenting the results of strength tests on thin-walled cylinders and truncated cones of circular and elliptical section; it comprises the results obtained to date from torsion (pure shear) tests on 65 thin-walled duralumin cylinders of circular section with ends clamped to rigid bulkheads. The effect of variations in the length/radius and radius/thickness ratios on the type of failure is indicated, and a semi-empirical equation for the shearing stress at maximum load is given.
    Type: NACA-TN-427
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  • 88
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    Comparative Performance of a Powerplus Vane-type Supercharger and an N.A.C.A. Roots-type Supercharger (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of tests of a Power plus supercharger and a comparison of its performance with the performance previously obtained with an N.A.C.A. Roots-type supercharger. The Powerplus supercharger is a positive displacement blower of the vane type having mechanically operated vanes, the movement of which is controlled by slots and eccentrics. The supercharger was tested at a range of pressure differences from 0 to 15 inches of mercury and at speeds from 500 to 2,500 r.p.m. The pressure difference across the supercharger was obtained by throttling the intake of a depression tank which was interposed in the air duct between the supercharger and the Durley orifice box used for measuring the air. The results of these tests show that at low pressure differences and at all speeds the power required by the Powerplus supercharger to compress a definite quantity of air per second is considerably higher than that required by the Roots. At pressure differences from 10 to 14 inches of mercury and at speeds over 2,000 r.p.m. the power requirements of the two superchargers are practically the same. At a pressure difference of 15 inches of mercury or greater and at a speed of 2,500 r.p.m. or greater the performance of the Powerplus supercharger is slightly better than that of the Roots. Because the Powerplus supercharger cannot be operated at a speed greater than 3,000 r.p.m. as compared with 7,000 r.p.m. for the Roots, its capacity is approximately one-half that of the Roots for the same bulk. The Powerplus supercharger is more complicated and less reliable than the Roots supercharger.
    Type: NACA-TN-426
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  • 89
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    Methods of Visually Determining the Air Flow Around Airplanes (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes methods used by the National Advisory Committee for Aeronautics to study visually the air flow around airplanes. The use of streamers, oil and exhaust gas streaks, lampblack and kerosene, powdered materials, and kerosene smoke is briefly described. The generation and distribution of smoke from candles and from titanium tetrachloride are described in greater detail because they appear most advantageous for general application. Examples are included showing results of the various methods.
    Type: NACA-TN-425
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  • 90
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    The pressure distribution over a modified elliptical wing tip on a biplane in flight (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note presents the results of flight pressure-distribution tests on the right upper wing panel of a Douglas M-3 airplane equipped with a modified elliptical tip having a slight amount of washout. The results are given in tables and curves in such form that the load distribution for any normal force coefficient within the usual range encountered in flight may be determined.
    Type: NACA-TN-387
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  • 91
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    Preliminary Photomicrographic Studies of Fuel Sprays (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Photomicrographs were taken of fuel sprays injected into air at various densities for the purpose of studying the spray structure and the stages in the atomization of the fuel. The photomicrographs were taken at magnifying powers of 2.5, 3.25, and 10, using a spark discharge of very short duration for illumination. The results indicate that the theory advanced by Dr. R. A. Castleman, Jr., on the atomization of fuel in carburetors may also be applied to the atomization of fuel sprays of the solid-injection type. The fuel leaves the nozzle as a solid column, is ruffled and then torn into small, irregular ligaments by the action of the air. These ligaments are then quickly broken up into drops by the surface tension of the fuel. The photomicrographs also show that the dispersion of a fuel spray at a given distance from the nozzle increases with an increase in the jet velocity or an increase in the air density. The first portions of fuel sprays injected from an automatic injection valve into air at atmospheric density have a much greater dispersion than the later portions, but this difference decreases rapidly as the air density is increased.
    Type: NACA-TN-424
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  • 92
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    Effect of length of Handley Page tip slots on the lateral-stability factor, damping in roll (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests have been made in the NACA 7 by 10 foot wind tunnel on a Clark Y wing model equipped with various lengths of Handley Page slots extending inward from the wing tips. The slot lengths tested ranged from 20 to 100 per cent of the semi span. The effect of slot lengths on damping in roll was determined by means of both free-autorotation and forced-rotation test. In addition, the maximum lift coefficient was found with each slot length. The optimum length of slot for satisfactory damping in roll over a large range of angles of attack was found to be slightly over 50 per cent of the semispan for the form of slot tested.
    Type: NACA-TN-423
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  • 93
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    Effect of nose shape on the characteristics of symmetrical airfoils (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests of nine symmetrical airfoils, having different leading-edge radii, were made in the variable density wind tunnel. Three symmetrical NACA airfoils having maximum thickness-to-chord ratio of 0.06, 0.012, and 0.018 were used as basic (or normal) sections; and for each of these thicknesses one thinner and one blunter nose section were developed. Although the slope of the lift curve varies with thickness, these tests show that for any given thickness the slope is independent of nose radius.
    Type: NACA-TN-386
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  • 94
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    Tests of six symmetrical airfoils in the variable density wind tunnel (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper is the first of a series covering an investigation of a family of airfoils all formed from a basic profile. It gives in preliminary form the results of six symmetrical airfoils, differing only in maximum thickness. The maximum thickness-to-chord ratios are 0.06, 0.09, 0.12, 0.15, 0.18, and 0.21.
    Type: NACA-TN-385
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  • 95
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    The aerodynamic characteristics of a model wing having a split flap deflected downward and moved to the rear (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were made on a model wing with three different sized split trailing-edged flaps, in the NACA 7 by 10 foot wind tunnel. The flaps were formed of the lower rear portion of the wing and were rotated downward about axes at their front edges. The lift, drag, and center of pressure were measured with the axis in its original position and also with it moved back in even steps to the trailing edge of the main wing, giving in effect an increase in area. The split flaps when deflected about their original axis locations gave slightly higher maximum lift coefficients than conventional trailing-edge flaps, and the lift coefficients were increased still further by moving the axes toward the rear. The highest value of C(sub L max), which was obtained with the largest flap hinged at 90 per cent of the chord from the leading edge, was 2.52 as compared with 1.27 for the basic wing.
    Type: NACA-TN-422
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  • 96
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    The pressure distribution over a long elliptical wing tip on a biplane in flight (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note presents the results of flight pressure-distribution tests on the right upper wing panel of a Douglas M-3 airplane equipped with an elliptical tip of length equal to the wing chord. The results are given in such form that the load distribution for any normal-force coefficient within the usual range encountered in flight may easily be determined.
    Type: NACA-TN-437
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  • 97
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    The Nature of Air Flow About the Tail of an Airplane in a Spin (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Air flow about the fuselage and empennage during a high-angle-of-attack spin was made visible in flight by means of titanium-tetrachloride smoke and was photographed with a motion-picture camera. The angular relation of the direction of the smoke streamer to the airplane axes was computed and compared with the angular direction of the motion in space derived from instrument measurement of the spin of the airplane for a nearly identical mass distribution. The results showed that the fin and upper part of the rudder were almost completely surrounded by dead air, which would render them inoperative; that the flow around the lower portion of the rudder and the fuselage was nonturbulent; and that air flowing past the cockpit in a high-angle-of-attack spin could not subsequently flow around control surfaces.
    Type: NACA-TN-421
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  • 98
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    Metal-truss wing spars (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The purpose of the study was to develop improvements in the current methods for the calculation of the loads in members of metal truss wing spars which are subjected to combined bending and compression. The theory developed here has two important practical applications. One is the calculation of the effective moment of inertia of a truss spar from the geometry of the spar and the loads to which the spar is to be subjected. The second is the determination of the most economical location of metal for stiffening a truss spar which has too much deflection.
    Type: NACA-TN-383
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  • 99
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    The Effect of Propellers and Nacelles on the Landing Speeds of Tractor Monoplanes (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper reports wind-tunnel tests giving the lift coefficients of large-scale wing-nacelle combinations both with and without the propeller. The tests were made to show the effect of nacelles, and idling and stopped propellers on the landing speeds of tractor monoplanes. Four types of nacelles with various cowlings were used in numerous positions with respect to both a Clark Y and a thick airfoil. The effect of both the idling and stopped propeller on lift, and consequently on landing speed, was negligible. A nacelle with exposed engine cylinders when placed directly in front of an airfoil caused a slight reduction in lift, consequently an increase in landing speed, over the condition with the wing alone. With this exception no appreciable effect on landing speed was indicated for any of the other combinations.
    Type: NACA-TN-420
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  • 100
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    Basic requirements of fuel-injection nozzles for quiescent combustion chambers (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents test results obtained during an investigation of the performance of a single-cylinder, high-speed, compression-ignition test engine when using multiple-orifice fuel-injection valve nozzles in which the number and the direction of the orifices were varied independently.
    Type: NACA-TN-382
    Format: application/pdf
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