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  • Other Sources  (185)
  • 1980-1984
  • 1930-1934  (185)
  • 1931  (185)
  • 1
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    [Neue Nr. 6014] Ober-Ingelheim / Geologische Karte (1931)
    Hessisches Landesamt für Bodenforschung, Wiesbaden
    In:  SUB Göttingen | KART B 104:6014 | KART H 86:6014
    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 007 50 - E 008 00 / N 050 00 - N 049 54.
    Description: DFG, SUB Göttingen
    Description: map
    Description: DFG, SUB Göttingen
    Keywords: ddc:912 ; ddc:554.3 ; Geologische Karte ; Ober-Ingelheim
    Language: German
    Type: doc-type:carthographicMaterial
    Format: 117
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    CITATION GEO-LEO
  • 2
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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
  • 3
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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
  • 4
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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
  • 5
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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
  • 6
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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
  • 7
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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
  • 8
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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
  • 9
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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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    BIBLIOGRAPHY SEISMOLOGY
  • 10
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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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    BIBLIOGRAPHY INKA BB
  • 11
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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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    BIBLIOGRAPHY INKA BB
  • 12
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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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    BIBLIOGRAPHY INKA BB
  • 13
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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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    BIBLIOGRAPHY INKA BB
  • 14
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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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    BIBLIOGRAPHY INKA BB
  • 15
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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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    BIBLIOGRAPHY INKA BB
  • 16
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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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    BIBLIOGRAPHY INKA BB
  • 17
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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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    BIBLIOGRAPHY INKA BB
  • 18
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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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    BIBLIOGRAPHY INKA BB
  • 19
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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
  • 20
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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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    BIBLIOGRAPHY SEISMOLOGY
  • 21
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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
  • 22
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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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    NASA TECHNICAL REPORTS
  • 23
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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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    NASA TECHNICAL REPORTS
  • 24
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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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    NASA TECHNICAL REPORTS
  • 25
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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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    NASA TECHNICAL REPORTS
  • 26
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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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    NASA TECHNICAL REPORTS
  • 27
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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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    NASA TECHNICAL REPORTS
  • 28
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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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    NASA TECHNICAL REPORTS
  • 29
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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
  • 30
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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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    NASA TECHNICAL REPORTS
  • 31
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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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    NASA TECHNICAL REPORTS
  • 32
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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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    NASA TECHNICAL REPORTS
  • 33
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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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  • 34
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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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  • 35
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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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  • 36
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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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  • 37
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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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    NASA TECHNICAL REPORTS
  • 38
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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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    NASA TECHNICAL REPORTS
  • 39
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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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  • 40
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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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  • 41
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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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  • 42
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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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  • 43
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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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  • 44
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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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  • 45
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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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  • 46
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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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  • 47
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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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  • 48
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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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  • 49
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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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  • 50
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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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  • 51
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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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  • 52
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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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  • 53
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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
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  • 54
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    Endurance and Other Properties at Low Temperatures of Some Alloys for Aircraft Use (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The low temperature endurance properties of materials for aircraft construction are not well known. In order to determine them, apparatus for testing endurance at -40 C has been devised. The endurance properties of monel metal, low-carbon stainless steel, "18 and *, " 3 1/2% Ni steel and chromium-molybdenum steel have been determined at -40 C and at room temperature about +20 C. Tensile, impact and hardness tests of these materials have also been made at various temperatures. The results show an increase in endurance limit, tensile strength, and hardness with decreased temperature. Impact strength is, in general, decreased, but of all the alloys tested, only one, low-carbon stainless steel, gives less than 15 ft. lb. Chrpay impact test at -40 C.
    Type: NACA-TN-381
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  • 55
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    A suggested method for measuring turbulence (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The desirability of a quantitative measure of turbulence is emphasized, and a possible method of attack on the problem is discussed. Data are presented to show that the hot-wire anemometer has possibilities as an instrument for measuring turbulence. An apparatus consisting essentially of two hot wire, one parallel to the air flow and one at right angles to it, is suggested.
    Type: NACA-TN-380
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  • 56
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    The pressure distribution over a semicircular wing tip on an airplane 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 semicircular wing tip. The results are given in tables and curves in such form that the load distribution for any force coefficient within the usual range encountered in flight may easily be determined.
    Type: NACA-TN-379
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  • 57
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    Comparison of weights of 17ST and steel tubular structural members used in aircraft construction (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Although the strong aluminum alloys have proved themselves to be very efficient in aircraft construction there is a growing competition from the high-strength steels for certain parts, especially for tubular members. This tendency is being reflected in research work carried on at the Bureau of Standards. This study will be based largely on data given in Technical Note No. 307 of the NACA.
    Type: NACA-TN-378
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  • 58
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    An integrating manometer for use in wind tunnel pressure distribution measurements (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A multiple manometer designed to integrate automatically the normal force over an airfoil section is described and its mathematical theory explained. The development of this instrument was conducted at the Langley Memorial Aeronautical Laboratory.
    Type: NACA-TN-377
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  • 59
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    Effect of High Air Velocities on the Distribution and Penetration of a Fuel Spray (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: By means of the NACA Spray Photography Equipment high speed moving pictures were taken of the formation and development of fuel sprays from an automatic injection valve. The sprays were injected normal to and counter to air at velocities from 0 to 800 feet per second. The air was at atmosphere temperature and pressure. The results show that high air velocities are an effective means of mixing the fuel spray with the air during injection.
    Type: NACA-TN-376
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  • 60
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    Moments of inertia of several airplanes (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper, which is the first of a series presenting the results of such measurements, gives the momental ellipsoids of ten army and naval biplanes and one commercial monoplane. The data were obtained by the use of a pendulum method, previously described. The moments of inertia are expressed in coefficient as well as in dimensional form, so that those for airplanes of widely different weights and dimensions can be compared.
    Type: NACA-TN-375
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  • 61
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    Preliminary Study of Applied Load Factors in Bumpy Air (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Theoretical relations involved in the study are reviewed to furnish a basis upon which experimental data can be properly analyzed. The structure of the atmosphere in relation to the load-factor problem is briefly discussed, and the acceleration data obtained on a number of flights with various airplanes are presented and analyzed to the extent that the results are applicable to n=any airplane.
    Type: NACA-TN-374
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  • 62
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    Investigation of the Discharge Rate of a Fuel-injection System (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In connection with the development of a method for analyzing indicator cards taken from high-speed compression-ignition engines, this investigation was undertaken to determine the average quantity of fuel discharged during each crank degree of injection period.
    Type: NACA-TN-373
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  • 63
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    Development of an Impinging-jet Fuel-injection Valve Nozzle (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: During an investigation to determine the possibilities and limitations of a two-stroke-cycle engine and ignition, it was necessary to develop a fuel injection valve nozzle to produce a disk-shaped, well dispersed spray. Preliminary tests showed that two smooth jets impinging upon each other at an angle of 74 degrees gave a spray with the desired characteristics. Nozzles were built on this basis and, when used in fuel-injection valves, produced a spray that fulfilled the original requirements. The spray is so well dispersed that it can be carried along with an air stream of comparatively low velocity or entrained with the fuel jet from a round-hole orifice. The characteristics of the spray from an impinging-jet nozzle limits its application to situations where wide dispersion is required by the conditions in the engine cylinder and the combustion chamber.
    Type: NACA-TN-372
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  • 64
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    Experiments with an Airfoil Model on which the Boundary Layers are Controlled Without the Use of Supplementary Equipment (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes test made in the Variable Density Wind Tunnel of the NACA to determine the possibility of controlling the boundary layer on the upper surface of an airfoil by use of the low pressure existing near the leading edge. The low pressure was used to induce flow through slots in the upper surface of the wing. The tests showed that the angle of attack for maximum lift was increased at the expense of a reduction in the maximum lift coefficient and an increase in the drag coefficient.
    Type: NACA-TN-371
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  • 65
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    Strength Tests on Paper Cylinder in Compression, Bending and Shear (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Static tests on paper cylinders were conducted at the Langley Memorial Aeronautical Laboratory at Langley Field, Virginia, to obtain qualitative information in connection with a study of the strength of stressed-skin fuselages. The effects of radius-thickness ratio and bulkhead spacing were investigated with the cylinders in compression, bending, combined bending and shear, and torsion.
    Type: NACA-TN-370
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  • 66
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    Effect of orifice length-diameter ratio on the coefficient of discharge of fuel-injection nozzles (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The variation of the coefficient of discharge with the length-diameter ratio of the orifice was determined for nozzles having single orifice 0.008 and 0.020 inch in diameter. Ratios from 0.5 to 10 were investigated at injection pressures from 500 to 5,000 pounds per square inch. The tests showed that, within the error of the observation, the coefficients were the same whether the nozzles were assembled at the end of a constant tube or in an automatic injection valve having a plain stem.
    Type: NACA-TN-369
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  • 67
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    The variation in pressure in the cabin of an airplane in flight (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The pressure in the cabin of a Fairchild cabin monoplane wa surveyed in flight, and was found to decrease with increased air speed over the fuselage and to vary with the number and location of openings in the cabin. The maximum depression of 2.2 inches of water (equivalent pressure altitude at sea level of 152 feet) occurred at the high speed of the airplane in level flight with the cabin closed.
    Type: NACA-TN-368
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  • 68
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    The aerodynamic characteristics of three tapered airfoils tested in the variable density wind tunnel (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report contains the lift, drag, and moment characteristics of tapered Clark Y, Gottingen 393, and USA 45 airfoils as obtained from tests made in the Variable Density Wind Tunnel of the NACA. The results are given at both low and high Reynolds Numbers to show scale effect and to provide data for use in airplane design.
    Type: NACA-TN-367
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  • 69
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    Some Characteristics of Fuel Sprays at Low-injection Pressures (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of tests conducted at the Langley Memorial Aeronautical Laboratory, Langley Field, Va., to determine some of the characteristics of the fuel sprays obtained from an 0.008-inch and a 0.020-inch open nozzle when injection pressures from 100 to 500 pounds per square inch were used. Fuel oil and gasoline were injected into air at densities of atmospheric land 0.325 pound per cubic foot. It was found that the penetration rate at these low pressures was about the same as the rate obtained with higher pressures. Spray cone-angles were small and individual oil drops were visible in all the sprays. Gasoline and fuel oil sprays had similar characteristics.
    Type: NACA-TN-399
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  • 70
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    Torsion in box wings (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Logical analysis of a box wing necessitates the allowance for the contribution of the drag spars to the torsional strength of the structure. A rigorous analysis is available in the use of the Method of Least Work. The best logical method of analysis is that applying Prandtl's Membrane Analogy. The results so obtained vary by a negligible amount from those obtained by the rigorous method.
    Type: NACA-TN-366
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  • 71
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    The Effect of Slots and Flaps on the Lift and Drag of the Mcdonnell Airplanes Determined in Flight (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note contains the results of flight test conducted by the National Advisory Committee for Aeronautics on a low-wing monoplane equipped with leading-edge slots extending over the entire wing and flaps extending only to the ailerons, to find their effect on the lift and drag characteristics of the airplane. Curves are given showing the lift and drag characteristics of the airplane for the following conditions of the slots and flaps neutral; slots closed and flaps down; and slots open and flaps down. In addition, the high and low speed in level flight and the climbing characteristics are given. The results show that the slots used alone increase the maximum lift coefficient 54 per cent; the flaps alone increase it 38 per cent; and the slots and flaps in combination decrease the landing speed from 60 to 43 m.p.h.; increase the speed range of the airplane 40 per cent; and increase the glide angle at landing speed 4.2 degrees.
    Type: NACA-TN-398
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  • 72
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    Interference Effects and Drag of Struts on a Monoplane Wing (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were conducted in the Variable Density Wind Tunnel of the NACA to determine the importance of the interference effects and drag of struts on a monoplane. Inclined struts were placed upon a Gottingen 387 airfoil in the lower surface positions and in two upper surface positions. Tests were made at values of Reynolds Number comparable with those obtained in flight. It was found that the interference drag of struts may be as great as the drag of the struts alone.
    Type: NACA-TN-365
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  • 73
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    The aerodynamic characteristics of six commonly used Airfoils over a large range of positive and negative angles of attack (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper presents the results of tests of six commonly used airfoils: the CYH, the N-22, the C-72, the Boeing 106, and the Gottingen 398. The lifts, drags, and pitching moments of the airfoils were measured through a large range of positive and negative angles of attack. The tests were made in the variable density wind tunnel of the National Advisory Committee for Aeronautics at a large Boeing 106, and the Gottingen 398 airfoils, the negative maximum lift coefficients were found to be approximately half the positive; but for the M-6 and the CYH, which have less effective values were, respectively, 0.8 and 0.6 of the positive values.
    Type: NACA-TN-397
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  • 74
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    Tests in the Variable Density Wind Tunnel to Investigate the Effects of Scale and Turbulence on Airfoil Characteristics (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effect of scale and turbulence on the lift and drag of five airfoils the NACA 0006, the NACA 0021, the Clark Y and the USA 35-A, and the USN PS6, have been investigated in the Variable Density Wind Tunnel of the NACA. Tests were made over a wide scale range for only two different conditions of turbulence.
    Type: NACA-TN-364
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  • 75
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    The Behavior of Conventional Airplanes in Situations Thought to Lead to Most Crashes (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Simple flight tests were made on ten conventional airplanes for the purpose of determining their action in the following two situations, which are generally thought to precede and lead to a large proportion of airplane crashes.
    Type: NACA-TN-363
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  • 76
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    The Interference Effects on an Airfoil of a Flat Plate at Mid-span Position (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report gives the results of an investigation of the mutual interference of an airfoil and a flat plate inserted at mid-span position. The tests were conducted in the Variable-Density Wind Tunnel of the National Advisory Committee for Aeronautics at a high value of the Reynolds Number. The interference effects of this combination were found to be small. Supplementary tests indicated that the use of fillets decreases both the lift and drag slightly. A bibliography of publication dealing with interference between wings and bodies, and with the effects of cut-outs and fillets is included.
    Type: NACA-TN-403
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  • 77
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    Lift and drag characteristics of a cabin monoplane (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results of flight tests conducted by the NACA to determine the lift and drag characteristics of a full-scale airplane are given herein. A Fairchild FC-2W2 cabin monoplane having a Gottingen 387 wing section was used for the tests. The maximum lift coefficient for the airplane is compared with that obtained for the Gottingen 387 airfoil in recent tests in the Variable Density Tunnel. The maximum lift coefficient for the airplane was found to be 1.50 and that for the airfoil 1.56. Although the flight tests were confined chiefly to glides with the propeller locked horizontally, data obtained with the propeller operating at zero thrust for a few angles of attack are also included.
    Type: NACA-TN-362
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  • 78
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    The effect of small variations in profile of airfoils (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report deals with the effect of small variations in ordinates specified by different laboratories for the airfoil section. This study was made in connection with a more general investigation of the effect of small irregularities of the airfoil surface on the aerodynamic characteristics of an airfoil. These tests show that small changes in airfoil contours, resulting from variations in the specified ordinates, have a sufficiently large effect upon the airfoil characteristics to justify the taking of great care in the specification of ordinates for the construction of models.
    Type: NACA-TN-361
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  • 79
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    Performance of a Compression-ignition Engine with a Precombustion Chamber Having High-Velocity Air Flow (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Presented here are the results of performance tests made with a single-cylinder, four stroke cycle, compression-ignition engine. These tests were made on a precombustion chamber type of cylinder head designed to have air velocity and tangential air flow in both the chamber and cylinder. The performance was investigated for variable load and engine speed, type of fuel spray, valve opening pressure, injection period and, for the spherical chamber, position of the injection spray relative to the air flow. The pressure variations between the pear-shaped precombustion chamber and the cylinder for motoring and full load conditions were determined with a Farnboro electric indicator. The combustion chamber designs tested gave good mixing of a single compact fuel spray with the air, but did not control the ensuing combustion sufficiently. Relative to each other, the velocity of air flow was too high, the spray dispersion by injection too great, and the metering effect of the cylinder head passage insufficient. The correct relation of these factors is of the utmost importance for engine performance.
    Type: NACA-TN-396
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  • 80
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    The effectiveness of a double-stem injection valve in controlling combustion in a compression-ignition engine (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was made to determine to what extent the rates of combustion in a compression-ignition engine can be controlled by varying the rates of fuel injection. The tests showed that the double-stem valve operated satisfactorily under all normal injection conditions; the rate of injection has a definite effect on the rate of combustion; the engine performance with the double-stem valve was inferior to that obtained with a single-stem valve; and the control of injection rates permitted by an injection valve of two stages of discharge is not sufficient to effect the desired rates of combustion.
    Type: NACA-TN-402
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  • 81
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    Tests of N.A.C.A. airfoils in the variable density wind tunnel Series 44 and 64 (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note is one of a series covering an investigation of a number of related airfoils. It presents the results obtained from tests in the N.A.C.A. Variable Density Wind Tunnel of two groups of six airfoils each. One group, the 44 series, has a maximum mean camber of 4 percent of the chord at a position 0.4 of the chord behind the leading edge and the other group, the 64 series, has a maximum mean camber of 6 percent of the chord at the same position. The members within each group differ only in maximum thickness, the maximum thickness/chord ratios being: 0.06, 0.09, 0.12, 0.15, 0.18, and 0.21. The results are analyzed with a view to indicating the variation of the aerodynamic characteristics with profile thickness for airfoils having a certain mean camber line form.
    Type: NACA-TN-401
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  • 82
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    Penetration and Duration of Fuel Sprays from a Pump Injection System (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: High-speed motion pictures were taken of individual fuel sprays from a pump injection system. The changes in the spray-tip penetration with changes in the pump speed, injection-valve opening and closing pressures, discharge-orifice area, injection-tube length and diameter, and pump throttle setting were measured. In addition, the effects of the variables on the time lag and duration of injection can be controlled by the dimensions of the injection tube, the area of the discharge orifice, and the injection-valve opening and closing pressures.
    Type: NACA-TN-395
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  • 83
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    Advantages of Oxide Films as Bases for Aluminum Pigmented Surface Coatings for Aluminum Alloys (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Both laboratory and weather-exposure corrosion tests showed conclusively that the protection afforded by aluminum pigmented spar varnish coatings applied to previously anodized aluminum surfaces was greatly superior to that afforded by the same coatings applied to surfaces which had simply been cleaned free from grease and not anodized.
    Type: NACA-TN-400
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  • 84
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    The Prevention of Ice Formation on Gasoline Tank Vents (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This investigation was conducted in the refrigerated wind tunnel at the Langley Memorial Aeronautical Laboratory, Langley Field, Va., to determine a suitable method for preventing the formation of ice on the vents of airplane gasoline tanks. Tests were made on a variety of vent forms arranged in a number of different orientations relative to the direction of the air stream. Both the size of the tube and its orientation were found to be of great importance. Small tubes, under equal circumstances, were found to freeze over far more rapidly than large ones. Tubes pointing downstream, or shielded in other ways, appear to be perfectly immune against this hazard. A tube 3/4 inch in diameter with the opening pointing downstream is finally recommended as being the safest choice of gas tank vent.
    Type: NACA-TN-394
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  • 85
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    The pressure distribution over a square wing tip on a biplane in flight (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note presents the results obtained in pressure distribution tests on the right upper panel of a Douglas M-3 airplane in flight. These tests are a part of an extensive investigation on the effect of changes in tip shape on the load distribution.
    Type: NACA-TN-360
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  • 86
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    An investigation of cotton for parachute cloth (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This is a resume of the work of the Bureau of Standards on a cotton parachute cloth for use as a substitute for silk in the event of an emergency curtailing the supply. Cotton yarn of high strength in proportion to its weight and otherwise specially suitable for parachute cloth was developed. Cloth woven from this yarn in the bureau mill was equal or superior to parachute silk in strength and tear resistance, met the requirements with respect to air permeability, and weighed only a few tenths of an ounce per square yard more than the silk cloth. Practical trials of cotton parachutes carried out by the Navy Department clearly indicate that the cotton parachute closely approaches the silk parachute in performance as to rate of descent, opening time, strength and ability to function when stored in the pack for sixty days. The increase in weight of the equipment resulting from the use of cotton cloth instead of silk is considered to be well within practicable limits. A specification for cotton parachute cloth and the way in which the requirements of the specification have been met are given. Cotton yarns suitable for parachute cloth are now being woven commercially in the United States.
    Type: NACA-TN-393
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  • 87
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    Tests of N.A.C.A. airfoils in the variable-density wind tunnel Series 45 and 65 (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note is one of a series covering an investigation of a number of related airfoils. It presents the results obtained from tests in N.A.C.A. Variable-Density Wind Tunnel of two groups of six airfoils each. One group, the 45 series, has a maximum mean camber of 4 per cent of the chord at a position 0.5 of the chord behind the leading edge, and the other group, the 65 series, has a maximum mean camber of 6 per cent of the chord at the same position. The members within each group differ only in maximum thickness, the maximum thickness/chord ratios being: 0.06, 0.09, 0.12, 0.15, 0.18, and 0.21. The results are analyzed with a view to indicating the variation of the aerodynamic characteristics with profile thickness for airfoils having a certain mean camber line form.
    Type: NACA-TN-392
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  • 88
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    Tests of N.A.C.A. airfoils in the variable-density wind tunnel Series 43 and 63 (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note is one of a series covering an investigation of a family of related airfoils. It gives in preliminary form the results obtained from tests in the N.A.C.A. Variable-Density Wind Tunnel of two groups of six airfoils each. One group, the 43 series, has a maximum mean camber of 4 per cent of the chord at a position 0.3 of the chord from the leading edge; the other group, the 63 series, has a maximum mean camber of 6 per cent of the chord at the same position. The members within each group differ only in maximum thickness, the maximum thickness/chord ratios being:0.06, 0.09, 0.12, 0.15, 0.18, and 0.21. The results are analyzed with a view to indicating the variation of the aerodynamic characteristics with profile thickness for airfoils having a certain mean camber line.
    Type: NACA-TN-391
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  • 89
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    A Method for Reducing the Temperature of Exhaust Manifolds (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes tests conducted at the Langley Memorial Aeronautical Laboratory on an "air-inducting" exhaust manifold for aircraft engines. The exhaust gases from each cylinder port are discharged into the throat of an exhaust pipe which has a frontal bellmouth. Cooling air is drawn into the pipe, where it surrounds and mixes with the exhaust gases. Temperatures of the manifold shell and of the exhaust gases were obtained in flight for both a conventional manifold and the air-inducting manifold. The air-inducting manifold was installed on an engine which was placed on a test stand. Different fuels were sprayed on and into the manifold to determine whether the use of this manifold reduced the fire hazard. The flight tests showed reductions in manifold temperatures of several hundred degrees, to values below the ignition point of aviation gasoline. On the test stand when the engine was run at idling speeds fuels sprayed into the manifold ignited. It is believed that at low engine speeds the fuel remained in the manifold long enough to become thoroughly heated, and was then ignited by the exhaust gas which had not mixed with cooling air. The use of the air-inducting exhaust manifold must reduce the fire hazard by virtue of its lower operating temperature, but it is not a completely satisfactory solution of the problem.
    Type: NACA-TN-390
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  • 90
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    The N.A.C.A. Apparatus for Studying the Formation and Combustion of Fuel Sprays and the Results from Preliminary Tests (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Described here is an apparatus for studying the formation and combustion of fuel sprays under conditions closely simulating those in a high speed compression-ignition engine. The apparatus consists of a single-cylinder modified test engine, a fuel injection system so designed that a single charge of fuel can be injected into the combustion chamber, an electric driving motor, and a high-speed photographic apparatus. The cylinder head of the engine has a vertical disk form of combustion chamber whose sides are glass windows. When the fuel is injected into the combustion chamber, motion pictures at the rate of 2000 per second are taken of the spray formation by means of spark discharges. When combustion takes place, the light of combustion is recorded on the same photographic film as the spray photographs. Included here are the results of some tests to determine the effect of air temperature, air flow, and nozzle design on the spray formation. The results show that the compression temperature has little effect on the penetration of the fuel spray, but does not affect the dispersion, that air velocities of about 300 feet per second are necessary to destroy the core of the spray, and that the effect of air flow on the spray is controlled to a certain extent by the design of the injection nozzle. The results on the combustion of the spray show that when ignition does not take place until after spray cut-off, the ignition may start almost simultaneously throughout the combustion chamber or at different points throughout the chamber. When ignition takes place before spray cut-off, the combustion starts around the edge of the spray and then spreads throughout the chamber.
    Type: NACA-TN-389
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  • 91
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    A comparison of the aerodynamic characteristics of the normal and three reflexed airfoils in the variable density wind tunnel (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was made of the aerodynamic effects of reflexing the trailing edge of three commonly used airfoils. Six airfoils were used in the investigation: three having the normal profiles of the Navy 60, the Boeing 106, and the Gottingen 398, and three having these profiles modified to obtain a reflexed trailing edge with the mean camber line changed to give Cmc/4=0. The tests were conducted at a value of the Reynolds Number of approximately 3,100,000 in the variable density wind tunnel of the National Advisory Committee for Aeronautics. Measurements of lift, drag, and pitching moment were made on each of the six airfoils. The expected reduction of the center of pressure travel was obtained. The maximum lift was reduced approximately 12 per cent and the minimum profile drag approximately 4 per cent.
    Type: NACA-TN-388
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  • 92
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    The transference of heat from a hot plate to an air stream (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The object of the present study was to define experimentally the field of temperature and velocity in a heated flat plate when exposed to an air stream whose direction is parallel to it, then calculate therefrom the heat transference and the friction past the flat plate, and lastly, compare the test data with the mathematical theory. To ensure comparable results, we were to actually obtain or else approximate: a) two-dimensional flow; b) constant plate temperature in the direction of the stream. To approximate the flow in two dimensions, we chose a relatively wide plate and measured the velocity and temperature in the median plane.
    Type: NACA-TM-614
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  • 93
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    Airplane landing gear (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents an investigation of the design and construction of various types of landing gears. Some of the items discussed include: chassises, wheels, shock absorbers (rubber disk and rubber cord), as well as oleopneumatic shock absorbers. Various types of landing gears are also discussed such as the Messier, Bendix, Vickers, and Bleriot.
    Type: NACA-TM-627
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  • 94
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    Superchargers (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: It seems hardly necessary to use a supercharger near sea level simply to mix the gases. The importance of the supercharger will increase with the use of heavy fuels. Before long we shall probably be using two-stroke-cycle and four-stroke-cycle scavenging engines on airplanes. In accord with the present tendency, we shall present here the French solutions of the problem in a practical rather than in a purely theoretical manner.
    Type: NACA-TM-631
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  • 95
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    Measurement of visibility from the pilot's cockpit on different airplane types (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A process for the measurement of the visibility of airplanes from the pilot's cockpit is developed. The apparatus necessary for the measurements was suitably constructed and measurements of the fields of vision were made with it. The visibilities of six airplanes of different types of construction and use were measured, as well as the visibility of an automobile for comparison. An attempt was made to establish minimum visibility requirements and to express the excellence of visibility by means of a numerical coefficient.
    Type: NACA-TM-646
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  • 96
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    Resistance of plates and pipes at high Reynolds numbers (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: It was learned that the law of resistance for high R values does not follow the simple powers, and that the powers, which can be obtained approximately for the velocity distribution, gradually change. Since, moreover, very important investigations have recently been made on the resistance of plates at very high R values, it seemed of interest to apply the above line of reasoning to the new general law of resistance. For this purpose, the resistance and velocity distribution along the plate must always be equal to the values of the pipe flow at the corresponding Reynolds number. We made two kinds of calculations, of which the one given here is the simpler and more practical and also agrees better with the experimental results.
    Type: NACA-TM-600
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  • 97
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    Flat sheet metal girders with very thin metal web. Part III : sheet metal girders with spars resistant to bending - the stress in uprights - diagonal tension fields (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report continues the work presented in NACA-TM 605 and expands the scope to include the change in specific number of wrinkles from direction x to z, so that b and f become variable in direction z. Moreover, it seems likely that b and f increase from the edge toward the center if the sheet is infinitely thin.
    Type: NACA-TM-606
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  • 98
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    Optico-photographic measurements of airplane deformations (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The deformation of aircraft wings is measured by photographically recording a series of bright shots on a moving paper band sensitive to light. Alternating deformations, especially vibrations, can thus be measured in operation, unaffected by inertia. A handy recording camera, the optograph, was developed by the static division of the D.V.L. (German Experimental Institute for Aeronautics) for the employment of this method of measurement on airplanes in flight.
    Type: NACA-TM-610
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  • 99
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    Development of a Non-autorotative Airplane Capable of Steep Landing (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In the following we develop a non-autorotating monoplane wing. The conditions imposed on such a wing, aside from its freedom from autorotation,with respect to its polars and its construction, are taken into account as far as possible. It is indicated that the autorotation characteristics of a wing are dependent upon the speed of air flow as well as on the angle of yaw. This report postulates the knowledge of the behavior of certain conventional wings of different chords and cambers with respect to their air loads at large angles of attack.
    Type: NACA-TM-650
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  • 100
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    An Investigation of the Effectiveness of Ignition Sparks (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effectiveness of ignition sparks was determined by measuring the volume (or mass) of hydrogen and of oxygen which combines at low pressures. The sparks were generated by a magneto and an ignition spark coil. It was found that with constant energy the amount of reaction increases as the capacitance component of the spark increases. The use of a series spark gap may decrease or increase the amount of reaction, the effect depending upon the amount and distribution of capacitance in the circuit. So far as the work has progressed, it has been found that sparks reported by other investigations as being most efficient for igniting lean mixtures cause the largest amount of reaction. Differences between the amount of reaction with a magneto spark and an ignition spark coil were noted. The method appears to offer a means of determining the most efficient spark generator for internal-combustion engines as well as determining a relation between the character of spark, energy, and effectiveness in igniting inflammable mixtures.
    Type: NACA-TR-359
    Format: application/pdf
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