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  • Weitere Quellen  (126)
  • 1950-1954
  • 1935-1939  (126)
  • 1935  (126)
  • 1
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    [Neue Nr. 6114] Wörrstadt / Geologische Karte (1935)
    Hessisches Landesamt für Bodenforschung, Wiesbaden
    In:  SUB Göttingen | KART B 104:6114
    Details
    Publikationsdatum: 2023-02-14
    Beschreibung: Geologische Karte 1: 25 000. Digitalisat des FID GEO (Fachinformationsdienst Geowissenschaften der festen Erde), erstellt durch das GDZ (Göttinger Digitalisierungszentrum), Karte aus dem Bestand der SUB Göttingen. Koordinaten Vorlage: E 08 00 - 08 10 / N 049 48 - 049 54.
    Beschreibung: DFG, SUB Göttingen
    Beschreibung: map
    Beschreibung: DFG, SUB Göttingen
    Schlagwort(e): ddc:912 ; ddc:554.3 ; ddc:943.2 ; Geologische Karte ; Wörrstadt
    Sprache: Deutsch
    Materialart: doc-type:carthographicMaterial
    Standort Signatur Erwartet Verfügbarkeit
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    CITATION GEO-LEO
  • 2
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    [Neue Nr. 5322] Lauterbach / Geologische Karte (1935)
    Staatsverlag, [Wiesbaden]
    In:  SUB Göttingen | KART B 104:5322 | KART H 86:5322
    Details
    Publikationsdatum: 2022-11-22
    Beschreibung: Geologische Karte 1: 25 000 mit Erläuterungen. Digitalisat des FID GEO (Fachinformationsdienst Geowissenschaften der festen Erde), erstellt durch das GDZ (Göttinger Digitalisierungszentrum), Karte aus dem Bestand der SUB Göttingen.
    Beschreibung: DFG, SUB Göttingen
    Beschreibung: map
    Beschreibung: DFG, SUB Göttingen
    Schlagwort(e): ddc:912 ; ddc:943.2 ; ddc:554.3 ; Lauterbach ; Geologische Karte
    Sprache: Deutsch
    Materialart: doc-type:carthographicMaterial
    Format: 112
    Standort Signatur Erwartet Verfügbarkeit
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    CITATION GEO-LEO
  • 3
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    On seismic waves (second paper) (1935)
    In:  Gerlands Beiträge zur Geophysik, Milano, Gustav Fischer, vol. 45, no. 3, pp. 280-360, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1935
    Schlagwort(e): Waves ; Seismology ; Review article
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 4
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    Seismic reflection profile across Los Angeles Basin (1935)
    In:  Geol. Soc. Am. Proc., Milano, Gustav Fischer, vol. 45, no. 3, pp. 327-328, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1935
    Schlagwort(e): Seismology ; Seismics (controlled source seismology) ; Reflection seismics
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 5
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    Love waves generated from a source of a certain depth (1935)
    In:  Bull. Earthq. Res. Inst., Luxembourg, Deutsche Geophys. Gesellschaft, vol. 13, no. 3, pp. 1-17, pp. 8045, (ISSN: 1340-4202)
    Details
    Publikationsdatum: 1935
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 6
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    Investigation of overthrust faults by seismic methods (1935)
    In:  Science, Potsdam, ZIPE, vol. 81, no. 23, pp. 384-386, pp. 5091692, (ISBN: 0-12-018847-3)
    Details
    Publikationsdatum: 1935
    Schlagwort(e): Seismology ; Seismics (controlled source seismology) ; Geol. aspects ; Tectonics
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 7
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    Velocities of elastic waves in rocks of various age and at various depth (1935)
    In:  Bull. Am. Ass. Petroleum Geologists, Milano, Gustav Fischer, vol. 19, no. 3, pp. 1842, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1935
    Schlagwort(e): Elasticity ; Velocity analysis ; Laboratory measurements
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 8
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    The age of the earth from the changes in its temperature and elastic properties (1935)
    In:  Science, Milano, Gustav Fischer, vol. 82, no. 3, pp. 52, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1935
    Schlagwort(e): Earth model, also for more shallow analyses ! ; Elasticity ; Geothermics ; Physical properties of rocks
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 9
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    Seismic reflection profile across Los Angeles Basin (1935)
    In:  Pan Am. Geologist, Milano, Gustav Fischer, vol. 63, no. 3, pp. 303, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publikationsdatum: 1935
    Schlagwort(e): Seismology ; Seismics (controlled source seismology) ; Reflection seismics
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 10
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    Die Temperaturabhängigkeit der Entwicklung der Nonne (Lymantria monacha L) und ihre bevölkerungswissenschaftliche Auswertung (1935)
    In:  Zeit. f. Angew. Entomologie XXI(3): 333-384
    Details
    Publikationsdatum: 1935
    Beschreibung: Charakterisierung des Zusammenhangs zwischen Temperatur und Auftreten des Schädlings Nonne (Lymantria monacha L.) durch einen Temperatursummenindex (Nonnentemperaturindex) KATASTER-BESCHREIBUNG: Ermittlung eines Temperaturindexes der eine Einteilung in Gefahrenklassen für das Auftreten erlaubt KATASTER-DETAIL:
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 11
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    Die Entwicklung der deutschen Ernteerträge (1935)
    In:  Wirtschaft und Statistik , 15, 662, Verlag für Sozialpolitik
    Details
    Publikationsdatum: 1935
    Beschreibung: Entwicklung der Erträge von Winterroggen, Winterweizen, Sommergerste, Hafer, Kartoffeln, Zuckerrüben, Wiesenheu, Kleeheu in den jeweiligen deutschen Anbaugebieten KATASTER-BESCHREIBUNG: kein Bezug zum Klima KATASTER-DETAIL:
    Schlagwort(e): Deutschland ; 1878-1935 ; Zuckerrüben ; Kartoffeln ; Ertrag ; Hafer ; Roggen ; Weizen ; Gerste
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 12
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    Die Häufigkeit nasser und dürrer Sommermonate in Sachsen (1935)
    In:  Der Kulturtechniker 38: 103-129
    Details
    Publikationsdatum: 1935
    Beschreibung: Bestimmung der Dürremonate in Sachsen im Rahmen der vom Deutschen Ausschuß für Kulturbauwesen in Auftrag gegebene Untersuchungen auch für alle anderen Regionen Deutschlands KATASTER-BESCHREIBUNG: Untersuchungen zu den Niederschlagsmengen an allen 98 Stationen in Sachsen für die Vegetationszeit, Dürrehäufigkeit von 12 von Hundert (westl. Ausläufer des Fichtelgebirges) bis hin zu 54 vH (südlich von Meißen, Hinweis auf die Höhenlage und Windverhältnisse KATASTER-DETAIL: Nied- (〈50mm, in den Monaten Mai-August), dann Dürremonat mit zu erwartenden Konsequenzen für die Landwirtschaft Nied+ (〉100mm in den Monaten Mai-August), dann Bezeichnung als nasser Monat, ebenfalls Folgen für die Produktivität
    Schlagwort(e): Sachsen ; 1891-1925 ; Klima ; Landwirtschaft ; Niederschlag ; Trockenheit ; Vegetationsperiode
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 13
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    Witterung und Wasserhaushalt im Odergebiet besonders im Jahr 1934 (1935)
    Details
    Publikationsdatum: 1935
    Beschreibung: Wärmejahr 1934, mit Angabe von Verdunstung Wasserständen und Hinweisen zu früheren Extremjahren KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE INKA BB
  • 14
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    Earthquake prediction (1935)
    In:  Science, Köln, Elsevier, vol. 82, no. E48, pp. 219-220, pp. 1015, (ISSN: 1340-4202)
    Details
    Publikationsdatum: 1935
    Schlagwort(e): Seismology ; Earthquake precursor: prediction research
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 15
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    Mitteilungen der Erdbebenwarte der Westfälischen Berggewerkschaftskasse in Bochum 1934/1935 (1935)
    Reismann-Grone-Verl.
    In:  Essen, Reismann-Grone-Verl., vol. 19, no. 22, pp. 662-664, (ISBN 1-4020-1244-6)
    Details
    Publikationsdatum: 1935
    Schlagwort(e): Rock bursts (see also ERDSTOSS and GEBIRGSSCHLAG) ; ERDSTOSS (see also rockburst and Gebirgsschlag) ; Lohr
    Standort Signatur Erwartet Verfügbarkeit
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    BIBLIOGRAFIE SEISMOLOGIE
  • 16
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    Methods employed in america for the experimental investigation of aerodynamic phenomena at high speeds (1935)
    In:  CASI
    Details
    Publikationsdatum: 2006-10-26
    Schlagwort(e): unknown
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 17
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    Direct broadcasting satellite for educational television - ETV (1935)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Schlagwort(e): GENERAL
    Materialart: NASA, Washington Digest of the Proc. of the Colloq. on Satellite Broadcasting; p 17-20
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 18
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    Bibliography of Aeronautics: 1932 (1935)
    In:  CASI
    Details
    Publikationsdatum: 2018-06-05
    Beschreibung: This Bibliography of Aeronautics for 1932 covers the aeronautical literature published from January 1 to December 31, 1932. The first Bibliography of Aeronautics was published by the Smithsonian Institution as volume 55 of the Smithsonian Miscellaneous Collections and covered the material published prior to June 30, 1909. Supplementary volumes of the Bibliography of Aeronautics for the subsequent years have been published by the National Advisory Committee for Aeronautics. The last preceding volume was for the calendar year 1931. As in the previous volumes, citations of the publications of all nations are included in the languages in which these publications originally appeared. The arrangement is in dictionary form with author and subject entry and one alphabetical arrangement. Detail in the matter of subject reference has been omitted on account of the cost of presentation, but an attempt has been made to give sufficient cross-reference for research in special lines.
    Schlagwort(e): Aeronautics (General)
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 19
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    The importance of auto-ignition lag in knocking (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Materialart: NACA-TN-452
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 20
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    Calculations of the Effect of Wing Twist on the Air Forces Acting on a Monoplane Wing (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A method is presented for calculating the aerodynamic forces on a moncylane wing, taking into account the elastic twisting of the wing due to these forces. The lift distribution along the span is calculated by the formulas of Amstutz as a function of the geometrical characteristics of the wing and of the twist at stations 60 and 90 percent of the semispan. The twist for a given lift distribution is calculated by means of influence lines. As a numerical example, the forces on a Swiss military D.2V airplane are calculated. Comparisons with the strip method and with the ordinary stress-analysis method are also given.
    Materialart: NACA-TN-520
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 21
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    Wind-tunnel Tests of a Wing with a Trailing-edge Auxiliary Airfoil Used as a Flap (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report gives the characteristics of a wing with an auxiliary airfoil mounted near its trailing edge and used as a flap. The tests were made with a 10 by 60 inch Clark Y main airfoil and an NACA 0012 flap having a chord equal to 15 percent of the main wing chord. The axis of the flap in all cases was on the flap chord and 20 percent back from its leading edge. The optimum location of the flap axis relative to the main wing for maximum lift was found to be 1.25 percent of the main wing chord behind the trailing edge and 2.5 percent below the chord. In this position C(sub L max) was increased from 1.250 (for the plain wing) to 1.810 at 45 degrees deflection of the flap and C(sub D min) was decreased form 0.0155 to 0.0146 at minus 5 degrees deflection, the coefficient in each case being based on the sum of the flap and wing areas. No serious adverse change in lateral stability was found to result from the use of the flap in the optimum position.
    Materialart: NACA-TN-524
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 22
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    The heat transfer of cooling fins on moving air (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The present report is a comparison of the experimentally defined temperature and heat output of cooling fins in the air stream with theory. The agreement is close on the basis of a mean coefficient of heat transfer with respect to the total surface. A relationship is established between the mean coefficient of heat transfer, the dimensions of the fin arrangement, and the air velocity.
    Materialart: NACA-TM-763
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 23
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    Effect of Aerodynamic Design on Glider Performance (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The performance of a glider is determined by means of the velocity polar, which represents the connection between horizontal and sinking speed. The mean sinking speed for a given speed range can be determined on the basis of the velocity polar. These data form the basis for the most propitious design of a performance-type glider with a view to long-distance flight.
    Materialart: NACA-TM-762
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 24
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    Reduction of lift of a wing due to its drag (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This analysis computes for a predetermined airfoil and given Reynolds Number the course of the "displacement thickness," i.e., the course of the layer by which the streamlines of the potential flow are pushed away from the wing through the frictional layer. The result is, to a certain extent, a new wing contour.
    Materialart: NACA-TM-781
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 25
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    Tests of Nacelle-Propeller Combinations in Various Positions with Reference to Wings IV : Thick Wing - Various Radial-Engine Cowlings - Tandem Propellers (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report is the fourth of a series giving the results obtained from wind tunnel tests to determine the interference lift and drag and propulsive efficiency of wing-nacelle-propeller combinations. Previous reports give the results of tests with tractor propellers with various forms of nacelles and engine cowlings. This report gives the results of tests of tandem arrangements of engines and propellers in 11 positions with reference to a thick wing.
    Materialart: NACA-TR-505
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 26
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    Computation of the two-dimensional flow in a laminar boundary layer (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A comparison is made of the boundary-layer flow computed by the approximate method developed by K. Pohlhausen with the exact solutions which have been published for several special cases. A modification of Pohlhausen's method has been developed which extends the range of application at the expense of some decrease in the accuracy of the approximations.
    Materialart: NACA-TR-497
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 27
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    The Physical Effects of Detonation in a Closed Cylindrical Chamber (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Detonation in the internal-combustion engine is studied as a physical process. It is shown that detonation is accompanied by pressure waves within the cylinder charge. Sound theory is applied to the calculation of resonant pressure-wave frequencies. Apparatus is described for direct measurement of pressure-wave frequencies. Frequencies determined from two engines of different cylinder sizes are shown to agree with the values calculated from sound theory. An outline of the theoretically possible modes of vibration in a right circular cylinder with flat ends is included. An appendix by John P. Elting gives a method of calculating pressure in the sound wave following detonation.
    Materialart: NACA-TR-493
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 28
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    Relation of Hydrogen and Methane to Carbon Monoxide in Exhaust Gases from Internal-Combustion Engines (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The relation of hydrogen and methane to carbon monoxide in the exhaust gases from internal-combustion engines operating on standard-grade aviation gasoline, fighting-grade aviation gasoline, hydrogenated safety fuel, laboratory diesel fuel, and auto diesel fuel was determined by analysis of the exhaust gases. Two liquid-cooled single-cylinder spark-ignition, one 9-cylinder radial air-cooled spark-ignition, and two liquid-cooled single-cylinder compression-ignition engines were used.
    Materialart: NACA-TR-476
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 29
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    Wing Pressure Distribution and Rotor-Blade Motion of an Autogiro as Determined in Flight (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents the results of tests in which the pressure distribution over the fixed wing of an autogiro was determined in both steady and accelerated flight. In the steady-flight condition, the rotor-blade motion was also measured. These data show that in steady flight the rotor speed as a function of the air speed is largely affected by the variation of the division of load between the rotor and the wing; as the load on the wing increases, the rotor speed decreases. In steady flight the presence of the slipstream increased both the wing lift at a given air speed and the maximum lift coefficient of the wing above the corresponding values without the slipstream. In abrupt high-speed turns, the wing attained a normal force coefficient of unity at almost the initial value of the air speed and experienced its maximum load before maximum acceleration occurred.
    Materialart: NACA-TR-475
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 30
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    Annual report of the National Advisory Committee for Aeronautics (20th).administrative report including Technical Report nos. 475 to 507 (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: 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.
    Materialart: NACA-AR-20
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 31
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    Wing-Fuselage Interference, Tail Buffeting, and Air Flow About the Tail of a Low-Wing Monoplane (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents the results of wind tunnel tests on a Mcdonnell Douglas airplane to determine the wing-fuselage interference of a low-wing monoplane. The tests included a study of tail buffeting and the air flow in the region of the tail. The airplane was tested with and without the propeller slipstream, both in the original condition and with several devices designed to reduce or eliminate tail buffeting. The devices used were wing-fuselage fillets, a NACA cowling, reflexed trailing edge of the wing, and stub auxiliary airfoils.
    Materialart: NACA-TR-482
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 32
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    Stability of Thin-Walled Tubes Under Torsion (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: In this report a theoretical solution is developed for the torsion on a round thin-walled tube for which the walls become unstable. The results of this theory are given by a few simple formulas and curves which cover all cases. The differential equations of equilibrium are derived in a simpler form than previously found, it being shown that many items can be neglected.
    Materialart: NACA-TR-479
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 33
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    Drag of Prestone and Oil Radiators on the YO-31A Airplane (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: At the request of the Army Air Corps tests were conducted on a mock-up of the YO-31A airplane to determine the drag of the prestone and oil radiators. The drag of the airplane was determined with both radiators exposed on the lower surface of the fuselage; with each radiator exposed; and with no radiators. The results show that at 120 m.p.h the oil radiator accounted for 2.8 percent of the drag of the complete airplane; the prestone radiator 8.3 percent; and both radiators together, 11.8 percent.
    Materialart: NACA-TN-549
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 34
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    Flight Tests of a Balanced Split Flap with Particular Reference to Rapid Operation (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The flight path of a small parasol monoplane equipped with a special type of balanced split flap was determined for a series of glides during which the time taken to deflect or retract the flap was varied from 1 to 15 seconds in order to study the effect of the time taken to complete a flap movement on the motion of an airplane between the start of a flap movement and the attainment of steady flight with the new flap setting. For flap movements accompanied by a change of lift characteristics, and consequently of velocity, there is an appreciable delay in obtaining a desired change in glide angle even though the flap is operated instantaneously. Immediate control of the glide path is obtained only when the speed is maintained during the flap movement. When the speed is changed, the deviation from the desired path during the transition increases in proportion to the rapidity with which the flap is moved so that, with a high-lift flap, abrupt retraction at speeds less than the minimum speed with the flap retracted may be dangerous if practiced close to the ground.
    Materialart: NACA-TN-548
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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    NASA TECHNICAL REPORTS
  • 35
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    Development of the NACA slot-lip aileron (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: An investigation of the undesirable delayed action, or lag, of the spoiler-type lateral control device led to the development of the NACA slot-lip aileron. The tests were made in the 7- by 10-foot wind tunnel with a 4- by 8-foot wing hinged at the tunnel jet boundary and taken of the motion of the control device under test and of the resulting wing motion. First, the lag, as affected by the fore-and-aft location of retractable ailerons or spoilers was determined. The lag was found to increase regularly as the spoiler was moved from the rear of the wing toward the front. Then a combination of spoilers and fixed slot was developed that, with the spoiler retracting into the forward part of the slot, reduced the time lag to a negligible value. In addition, an arrangement was developed using a hinged aileron-type flap as the upper portion, or lip, of a slot through the wing. This arrangement appears to be usable as a form of lateral control device that shows promise of giving improved control and stability at the high angles of attack through stall, with negligible lag, low control forces, and relatively simple construction.
    Materialart: NACA-TN-547
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  • 36
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    Comparative Tests of Pitot-static Tubes (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Comparative tests were made on seven conventional Pitot-static tubes to determine their static, dynamic, and resultant errors. The effect of varying the dynamic opening, static opening, wall thickness, and inner-tube diameter was investigated. Pressure-distribution measurements showing stem and tip effects were also made. A tentative design for a standard Pitot-static tube for use in measuring air velocity is submitted.
    Materialart: NACA-TN-546
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  • 37
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    Tank Tests of a Model of a Flying-boat Hull Having a Longitudinally Concave Planing Bottom (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The NACA model 11-B, which has a longitudinally concave planing bottom forward of the step, was tested over a wide range of loading. The results of the tests are presented as curves of resistance and trimming moment plotted against speed for various trim angles and as curves of resistance coefficient at best trim angle, and trimming-moment coefficient. The characteristics of the form at the optimum trim are compared with those of NACA model 11-C which has the same form with the exception of a planing bottom longitudinally straight near the step. Photographs of the models being towed in the tank are included for a comparison of the spray patterns. At the best angles of trim in each case model 11-B has lower resistance at high speeds, a higher maximum positive trimming moment near the hump speed, and a more favorable spray pattern than of model 11-C.
    Materialart: NACA-TN-545
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  • 38
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    The Compressibility Burble (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Simultaneous air-flow photographs and pressure-distribution measurements have been made of the NACA 4412 airfoil at high speeds in order to determine the physical nature of the compressibility burble. The flow photographs were obtained by the Schlieren method and the pressures were simultaneously measured for 54 stations on the 5-inch-chord wing by means of a multiple-tube photographic manometer. Pressure-measurement results and typical Schlieren photographs are presented. The general nature of the phenomenon called the "compressibility burble" is shown by these experiments. The source of the increased drag is the compression shock that occurs, the excess drag being due to the conversion of a considerable amount of the air-stream kinetic energy into heat at the compression shock.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TN-543
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  • 39
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    An Application of the Von Karman-millikan Laminar Boundary-layer Theory and Comparison with Experiment (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The von Karman-Millikan theory of laminar boundary layers presented in NACA Technical Report No. 504 is applied to the laminar boundary layer about an elliptic cylinder on which boundary-layer and pressure-distribution measurements were made. An outline of the procedure of the von Karman-Millikan method is given. Good agreement is obtained between the calculated and experimental results, indicating that the method may be applied generally to the laminar boundary layer about any body provided that an experimentally determined pressure distribution is available. It appears that for all Reynolds Number above 24,000 the separation point for the elliptic cylinder should occur at a constant distance behind the point of minimum pressure, provided that the boundary layer does not become turbulent.
    Materialart: NACA-TN-544
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  • 40
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    The initial torsional stiffness of shells with interior webs (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A method of calculating the stresses and torsional stiffness of thin shells with interior webs is summarized. Comparisons between experimental and calculated results are given for 3 duralumin beams, 5 stainless steel beams and 2 duralumin wings. It is concluded that if the theoretical stiffness is multiplied by a correction factor of 0.9, experimental values may be expected to check calculated values within about 10 percent.
    Materialart: NACA-TN-542
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  • 41
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    The Effect of the Angle of Afterbody Keel on the Water Performance of a Flying-Boat Hull Model (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: NACA model 11-C was tested according to the general method with the angle of afterbody keel set at five different angles from 2-1/2 degrees to 9 degrees, but without changing other features of the hull. The results of the tests are expressed in curves of test data and of non-dimensional coefficients. At the depth of step used in the tests, 3.3 percent beam, the smaller angles of afterbody keel give greater load-resistance ratios at the hump speed and smaller at high speed than the larger angles of afterbody keel. Comparisons are made of the load-resistance ratios at several other points in the speed range. The effect of variation of the angle of afterbody keel upon the take-off performance of a hypothetical flying boat of 15,000 pounds gross weight having a hull of model 11-C lines is calculated, and the calculations show that the craft with the largest of the angles of afterbody keel tested, 9 degrees, takes off in the least time and distance.
    Schlagwort(e): Aircraft Design, Testing and Performance
    Materialart: NACA-TN-541
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  • 42
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    A deflection formula for single-span beams of constant section subjected to combined axial and transverse loads (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: In this paper there is presented a deflection formula for single-span beams of constant section subjected to combined axial and transverse loads of the types commonly encountered in airplane design. The form of the equation is obtainable by dimensional analysis. Tables and curves of the non dimensional coefficients are appended to facilitate the use of the formula. The equation is applied to the determination of the spring constant of a beam. Tables and curves are presented to show the variation of the spring constant with changes in the axial load and position along the beam.
    Materialart: NACA-TN-540
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  • 43
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    Aerodynamic characteristics of several airfoils of low aspect ratio (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This paper presents the results of wind-tunnel tests of several airfoils of low aspect ratio. The airfoils included three circular Clark Y airfoils with different amounts of dihedral, two Clark Y airfoils with slots in their portions, and three flat-plate airfoils. Lift, drag, and pitching-moment characteristics of the slotted airfoils with slots open and closed; pitching moment characteristics of one of the slotted airfoils with slots open and closed; and lift characteristics of the flat-plate airfoils are included. The results reveal a definite improvement of lift, drag, and pitching-moment characteristics with increase in dihedral of the circular Clark Y wing. Lift characteristics near the stall were found to depend markedly on the shape of the extreme tip but were not greatly affected by slots through the after portion of the airfoils. Changes in plan form of the flat-plate airfoils gave erroneous indications of the effect to be expected from changes in plan form of an airfoil of Clark Y section. The minimum drag characteristics of the circular Clark Y airfoils were found to be substantially the same as for a Clark Y airfoil of conventional aspect ratio.
    Materialart: NACA-TN-539
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  • 44
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    A General Tank Test of NACA Model 11-C Flying-boat Hull, Including the Effect of Changing the Plan Form of the Step (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The results of a general tank test model 11-C, a conventional pointed afterbody type of flying-boat hull, are given in tables and curves. These results are compared with the results of tests on model 11-A, from which model 11-C was derived, and it is found that the resistance of model 11-C is somewhat greater. The effect of changing the plan form of the step on model 11-C is shown from the results of tests made with three swallow-tail and three pointed steps formed by altering the original step of the model. These results show only minor differences from the results obtained with the original model.
    Materialart: NACA-TN-538
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  • 45
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    A preliminary determination of normal accelerations on racing airplanes (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Rules and methods for insuring safe structural strength of racing airplanes used in the major air meets in this country have recently been considered. Acceleration records made in racing airplanes during actual air races were therefore considered desirable, and the NACA undertook the measurement of acceleration of loads on airplanes during all conditions of flight. Accelerations were measured on four airplanes at the Miami All-American Races in January 1934 and January 1935. The airplanes were representative of the fastest limited and unlimited displacement racing airplanes in current use in this country. Records during two races, or flights, on the race course were obtained with each airplane. The maximum normal acceleration recorded was 6.2g and the minimum was -1.2g.
    Materialart: NACA-TN-537
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  • 46
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    The 6-foot-4-inch Wind Tunnel at the Washington Navy Yard (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The 6-foot-4-inch wind tunnel and its auxiliary equipment has proven itself capable of continuous and reliable output of data. The real value of the tunnel will increase as experience is gained in checking the observed tunnel performance against full-scale performance. Such has been the case of the 8- by 8-foot tunnel, and for that reason the comparison in the calibration tests have been presented.
    Materialart: NACA-TN-536
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  • 47
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    The effect of depth of step on the water performance of a flying-boat hull model (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: NACA model 11-C was tested with four different depths of step to obtain information as to the effect of the depth of step on the water performance. The depths of step were selected to cover the practicable range of depths and in each case the included angle between the forebody and afterbody keels was kept the same 6-1/2 degrees. Small depths of step were found to give lower resistance at speeds below and at the hump speed of the model and greater depths of step lower resistance at high speeds. For low resistance throughout the speed range of the model investigated the most desirable depth of step is from 2.5 to 4.0 percent of the beam. The change of the best trim angle caused by variation of the depth of step was not appreciable. Increased depth of step caused increases in the maximum positive trimming moments at all trim angles investigated.
    Materialart: NACA-TN-535
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  • 48
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    Principal Effects of Axial Load on Moment-Distribution Analysis of Rigid Structures (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This thesis presents the method of moment distribution modified to include the effect of axial load upon the bending moments. This modification makes it possible to analyze accurately complex structures, such as rigid fuselage trusses, that heretofore had to be analyzed by approximate formulas and empirical rules. The method is simple enough to be practicable even for complex structures, and it gives a means of analysis for continuous beams that is simpler than the extended three-moment equation now in common use. When the effect of axial load is included, it is found that the basic principles of moment distribution remain unchanged, the only difference being that the factors used, instead of being constants for a given member, become functions of the axial load. Formulas have been developed for these factors, and curves plotted so that their applications requires no more work than moment distribution without axial load. Simple problems have been included to illustrate the use of the curves.
    Materialart: NACA-TN-534
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  • 49
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    The thermodynamics of combustion in the Otto cycle engine (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Materialart: NACA-TN-533
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  • 50
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    Method of Testing Oxygen Regulators (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Oxygen regulators are used in aircraft to regulate automatically the flow of oxygen to the pilot from a cylinder at pressures ranging up to 150 atmospheres. The instruments are adjusted to open at an altitude of about 15,000 ft. and thereafter to deliver oxygen at a rate which increases with the altitude. The instruments are tested to determine the rate of flow of oxygen delivered at various altitudes and to detect any mechanical defects which may exist. A method of testing oxygen regulators was desired in which the rate of flow could be determined more accurately than by the test method previously used (reference 1) and by which instruments defective mechanically could be detected. The new method of test fulfills these requirements.
    Materialart: NACA-TN-532
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  • 51
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    Tank Tests of Model 11-G Flying-boat Hull (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The NACA model 11-G flying-boat hull, a modification of NACA model 11-A was tested over a range of loadings. The planing bottom of model 11-G has a variable-radius flare, or concavity, at the chines in contrast to the straight V planing bottom of model 11-A. The results are given as curves of resistance and trimming moment plotted against speed for various angles of trim. The characteristics of the form at the optimum angles of trim are given in non-dimensional form as curves of resistance coefficient, best trim angle, and trimming-moment coefficient plotted against speed coefficient. As compared with the original form, model 11-G is shown to have higher resistance at all loads and speeds and higher maximum trimming moments at heavy loads. The spray pattern, however, is generally more favorable, indicating that the service performance of model 11-A would be improved by some form of chime flare.
    Materialart: NACA-TN-531
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  • 52
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    Bending stresses due to torsion in cantilever box beams (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The paper beings with a brief discussion on the origin of the bending stresses in cantilever box beams under torsion. A critical survey of existing theory is followed by a summary of design formulas; this summary is based on the most complete solution published but omits all refinements considered unnecessary at the present state of development. Strain-gage tests made by NACA to obtained some experimental verification of the formulas are described next. Finally, the formulas are applied to a series of box beams previously static-tested by the U.S. Army Air Corps; the results show that the bending stresses due to torsion are responsible to a large extent for the free-edge type of failure frequently experienced in these tests.
    Materialart: NACA-TN-530
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  • 53
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    Analysis of a Strut with a Single Elastic Support in the Span, with Applications to the Design of Airplane Jury-strut Systems (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Materialart: NACA-TN-529
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  • 54
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    Wind-tunnel Tests of a Cyclogiro Rotor (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: During an extensive study of all types of rotating wings, the NACA examined the cyclogiro rotor and made an aerodynamic analysis of that system (reference 1). The examination disclosed that such a machine had sufficient promise to justify an experimental investigation; a model with a diameter and span of 8 feet was therefore constructed and tested in the 20-foot wind tunnel during 1934. The experimental work included tests of the effect of the motion upon the rotor forces during the static-lift and forward-flight conditions at several rotor speeds and the determination of the relations between the forces generated by the rotor and the power required by it.
    Materialart: NACA-TN-528
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  • 55
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    Strength Tests of Thin-walled Duralumin Cylinders of Elliptic Section (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report is the fifth of a series presenting the results of strength tests of thin-walled cylinders and truncated cones of circular and elliptic section; it includes the results obtained from torsion tests on 30 cylinders, pure bending tests on 30 cylinders, and combined transverse shear and bending tests on 60 cylinders. All the cylinders tested were elliptic section with the ends clamped to rigid bulkheads. In the pure bending and combined transverse shear and bending tests the loads were applied in the plane of the major axis. The results of the tests on elliptic cylinders are correlated with the results of corresponding tests on circular cylinders and are presented in charts suitable for use in design.
    Materialart: NACA-TN-527
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  • 56
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    Spinning characteristics of wings II : rectangular Clark Y biplane cellule: 25 percent stagger; 0 degree decalage; gap/chord 1.0 (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: General methods of theoretical analysis of airplane spinning characteristics have been available for some time. Some of these methods of analysis might be used by designers to predict the spinning characteristics of proposed airplane designs if the necessary aerodynamic data were known. The present investigation, to determine the spinning characteristics of wings, is planned to include variations in airfoil sections, plan forms, and tip shapes of monoplane wings and variations in stagger, gap, and decalage for biplane cellules. The first series of tests, made on a rectangular Clark Y monoplane wing, are reported in reference 1. That report also gives an analysis of the data for predicting the probable effects of various important parameters on the spin for normal airplanes using such a wing. The present report is the second of the series. It gives the aerodynamic characteristics of a rectangular Clark Y biplane cellule in spinning attitudes and includes a discussion of the data, using the method of analysis given in reference 1.
    Materialart: NACA-TN-526
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  • 57
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    The Aerodynamic Drag of Flying-boat Hull Model as Measured in the NACA 20-foot Wind Tunnel I. (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Measurements of aerodynamic drag were made in the 20-foot wind tunnel on a representative group of 11 flying-boat hull models. Four of the models were modified to investigate the effect of variations in over-all height, contours of deck, depth of step, angle of afterbody keel, and the addition of spray strips and windshields. The results of these tests, which cover a pitch-angle range from -5 to 10 degrees, are presented in a form suitable for use in performance calculations and for design purposes.
    Materialart: NACA-TN-525
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  • 58
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    Strength Tests of Thin-walled Duralumin Cylinders in Combined Transverse Shear and Bending (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report is the fourth of a series presenting the results of strength tests on thin-walled cylinders and truncated cones of circular and elliptic section; it includes the results on 100 thin-walled duralumin cylinders of circular section with ends clamped to rigid bulkheads. The tests show that as the ratio of moment to shear varies from small to large values the failure changes from a shear to a bending type. In the report a chart is presented that shows the corresponding changes in strength.
    Materialart: NACA-TN-523
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  • 59
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    Tank tests of a model of a flying-boat hull with a fluted bottom (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A 1/5-scale model of a flying-boat hull having flutes in the bottom both forward and aft of the step (NACA model 19) was tested to determine its water performance. The model was also tested after the successive removal of the flutes on the afterbody and forebody. The results from these tests are compared with those from tests of a model of the hull of the Navy PN-8 flying boat and it is concluded that the fluted-bottom model and its modifications are inferior to the model of the PN-8.
    Materialart: NACA-TN-522
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  • 60
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    Full-scale Force and Pressure-distribution Tests on a Tapered U.S.A. 45 Airfoil (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents the results of force and pressure-distribution tests on a 2:1 tapered USA 45 airfoil as determined in the full-scale wind tunnel. The airfoil has a constant-chord center section and rounded tips and is tapered in thickness from 18 percent at the root to 9 percent at the tip. Force tests were made throughout a Reynolds Number range of approximately 2,000,000 to 8,000,000 providing data on the scale effect in addition to the conventional characteristics. Pressure-distribution data were obtained from tests at a Reynolds Number of approximately 4,000,000. The aerodynamic characteristics given by the usual dimensionless coefficients are presented graphically.
    Materialart: NACA-TN-521
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  • 61
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    Vortex Noise from Rotating Cylindrical Rods (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A series of round rods of the some diameter were rotated individually about the mid-point of each rod. Vortices are shed from the rods when in motion, giving rise to the emission of sound. With the rotating system placed in the open air, the distribution of sound in space, the acoustical power output, and the spectral distribution have been studied. The frequency of emission of vortices from any point on the rod is given by the formula von Karman. From the spectrum estimates are made of the distribution of acoustical power along the rod, the amount of air concerned in sound production, the "equivalent size" of the vortices, and the acoustical energy content for each vortex.
    Materialart: NACA-TN-519
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  • 62
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    Performance tests of a single-cylinder compression-ignition engine with a displacer piston (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Engine performance was investigated using a rectangular displacer on the piston crown to cause a forced air flow in a vertical-disk combustion chamber of a single-cylinder, 4-stroke-cycle compression-ignition engine. The optimum air-flow area was determined first with the area concentrated at one end of the displacer and then with the area equally divided between two passages, one at each end of the displacer. Best performance was obtained with the two-passage air flow arranged to give a calculated maximum air-flow speed of 8 times the linear crank-pin speed. With the same fuel-spray formation as used without the air flow, the maximum clear exhaust brake mean effective pressure at 1,500 r.p.m. was increased from 90 to 115 pounds per square inch and the corresponding fuel consumption reduced from 0.46 to 0.43 pound per brake horsepower-hour. At 1,200 r.p.m., a maximum clear exhaust brake mean effective pressure of 120 pounds per square inch was obtained at a fuel consumption of 0.42 pound per brake horsepower-hour. At higher specific fuel consumption the brake mean effective pressure was still increasing rapidly.
    Materialart: NACA-TN-518
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  • 63
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    Propeller Vibrations and the Effect of the Centrifugal Force (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A method has been devised for determining the frequencies of the various modes of a stationary propeller and the associated crankshaft. A method has also been devised to obtain the effect of the centrifugal force on a revolving propeller by use of a flexible model.
    Materialart: NACA-TN-516
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  • 64
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    The Aerodynamic Forces and Moments on a Spinning Model of the F4B-2 Airplane as Measured by the Spinning Balance (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The aerodynamic forces and moments on a 1/12-scale model of the F4B-2 airplane were measured with the spinning balance in nine spinning attitudes with three sets of tail surfaces, namely, F4B-2 surfaces; F4B-4 fin and rudder with rectangular stabilizer; and with all tail surfaces removed. In one of these attitudes measurements were made to determine the effect upon the forces and moments of independent and of simultaneous displacement of the rudder and elevator for two of the sets of tail surfaces. Additional measurements were made for a comparison of model and full-scale data for six attitudes that were determined from flight tests with various control settings. The characteristics were found to vary in the usual manner with angle of attack and sideslip. The F4B-2 surfaces were quite ineffective as a source of yawing moments. The F4B-4 fin and F4B-2 stabilizer gave a greater damping yawing moment when controls were against the spin than did the F4B-2 surfaces but otherwise there was little difference. Substitution of a rectangular stabilizer for the F4B-2 stabilizer made no appreciable difference in the coefficient. Further comparisons with other airplane types are necessary before final conclusions can be drawn as to the relations between model and full-scale spin measurements.
    Materialart: NACA-TN-517
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  • 65
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    Tests of Spheres with Reference to Reynolds Number, Turbulence, and Surface Roughness (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The behavior of the Reynolds Number of the sphere is explained (in known manner) with the aid of the boundary-layer theory. Rear spindles may falsify, under certain conditions, the supercritical sphere drag, while suspension wires in the space behind the sphere leave no traceable influence. The critical Reynolds Number of the sphere was arrived at by an unconventional method; that is, by determining the critical wind speed at which the static pressure at the back of the sphere is the same as that of the undisturbed flow. The method makes it possible to interpret the critical Reynolds Number with only one test station.
    Materialart: NACA-TM-777
    Format: application/pdf
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  • 66
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    Method for the determination of the spanwise lift distribution (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The method for determination of the spanwise lift distribution is based on the Fourier series for the representation of the lift distribution. The lift distribution, as well as the angle of attack, is split up in four elementary distributions. The insertion of the angle-of-attack distribution in the Fourier series for the lift distribution gives a compound third series which is of particular advantage for the determination of the lift distribution. The method is illustrated in an example and supplemented by a graphical method. Lastly, the results of several comparative calculations with other methods are reported.
    Materialart: NACA-TM-778
    Format: application/pdf
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  • 67
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    Glider Development in Germany : a Technical Survey of Progress in Design in Germany Since 1922 (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report is a recounting of glider development beginning with the "Vampyr" on up to the present day.
    Materialart: NACA-TM-780
    Format: application/pdf
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  • 68
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    Weldability of High-tensile Steels from Experience in Airplane Construction, with Special Reference to Welding Crack Susceptibility (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The concept of welding crack tendency is explained and illustrated with practical examples. All pertinent causes are enumerated, and experimental measures are given through which the secondary effects can be removed and the principal causes analyzed: 1) welding stresses; and 2) material defects. The variations in length and stresses incident to welding a small bar as free weld, with restrained elongation and restrained elongation and contraction, are explored in three fundamental experiments.
    Materialart: NACA-TM-779
    Format: application/pdf
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  • 69
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    Full-Scale Wind-Tunnel Tests of a PCA-2 Autogiro Rotor (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents the results of force tests on and air-flow surveys near PCA-2 autogiro rotor in the NACA full-scale wind tunnel. The force tests were made at three pitch settings and several rotor speeds; the effect of fairing protuberances on the rotor blade was determined. Induced downwash and yaw angles were determined at low tip-speed ratios in a plane 1 1/2 feet above the path of the blade tips. The results show that the maximum l/d of the rotor cannot be appreciably increased by increasing the blade pitch angle above about 4.5 degrees at the blade tip; that the protuberances on the blades cause more than 5 percent of the total rotor drag; and that the rotor center-of-pressure travel is very small.
    Materialart: NACA-TR-515
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  • 70
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    Improved Airplane Windshields to Provide Vision in Stormy Weather (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents the results of wind tunnel tests to determine possible improvements in the design of airplane windshields, particularly with respect to the pilot's vision from the cabin in stormy weather.
    Materialart: NACA-TR-498
    Format: application/pdf
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  • 71
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    Vibration Response of Airplane Structures (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents test results of experiments on the vibration-response characteristics of airplane structures on the ground and in flight. It also gives details regarding the construction and operation of vibration instruments developed by the National Advisory Committee for Aeronautics.
    Materialart: NACA-TR-491
    Format: application/pdf
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  • 72
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    Tests of 16 related airfoils at high speed (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: In order to provide information that might lead to the development of better propeller section, 13 related symmetrical airfoils were tested in the NACA high-speed wind tunnel for a study of the effect of thickness form on the aerodynamic characteristics. The thickness-form variables studies were the value of the maximum thickness, the position along the chord at which the maximum thickness occurs, and the value of the leading-edge radius. The tests were conducted through the low angle-of-attack range for speeds extending from 35 percent of that of sound to slightly in excess of the speed at which a compressibility burble, or breakdown of flow, occurs. The corresponding Reynolds number range is 350,000 to 750,000.
    Materialart: NACA-TR-492
    Format: application/pdf
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  • 73
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    The Weathering of Aluminum Alloy Sheet Materials Used in Aircraft (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents the results of an investigation of the corrosion of aluminum alloy sheet materials used in aircraft. It has for its purpose to study the causes of corrosion embrittlement in duralumin-type alloys and the development of methods for its elimination. The report contains results, obtained in an extensive series of weather-exposure tests, which reveal the extent to which the resistance of the materials to corrosion was affected by variable factors in their heat treatment and by the application of various surface protective coatings. The results indicate that the sheet materials are to be regarded as thoroughly reliable, from the standpoint of their permanence in service, provided proper precautions are taken to render them corrosion-resistant.
    Materialart: NACA-TR-490
    Format: application/pdf
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  • 74
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    Heat Transfer from Finned Metal Cylinders in an Air Stream (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents the results of tests made to supply design information for the construction of metal fins for the cooling of heated cylindrical surfaces by an air stream. A method is given for determining fin dimensions for a maximum heat transfer with the expenditure of a given amount of material for a variety of conditions of air flow and metals.
    Materialart: NACA-TR-488
    Format: application/pdf
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  • 75
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    Air Conditions Close to the Ground and the Effect on Airplane Landings (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents the results of an investigation undertaken to determine the feasibility of making glide landings in gusty air. Wind velocities were measured at several stations between the ground and a height of 51 feet, and flight tests were made to determine the actual influence of gusts on an airplane gliding close to the ground.
    Materialart: NACA-TR-489
    Format: application/pdf
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  • 76
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    Infrared radiation from explosions in a spark-ignition engine (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents the results of an investigation to determine the variations in intensity and spectral distribution of the radiant energy emitted by the flames during normal and knocking explosions in an engine. Radiation extending into the infrared was transmitted by a window of fluorite, placed either near the spark plug or over the detonation zone at opposite ends of the combustion chamber. Concave, surface-silvered mirrors focused the beam, first at the slit of a stroboscope which opened for about 2 degrees of crank angle at any desired point in the engine cycle, and then upon the target of a sensitive thermocouple for measuring radiation intensity. Spectral distribution of the radiant energy was determined by placing over the window, one at a time, a series of five filters selected with a view to identifying, as far as possible without the use of a spectrograph, the characteristic emissions of water vapor, carbon dioxide, and incandescent carbon.
    Materialart: NACA-TR-486
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  • 77
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    Effect of Moderate Air Flow on the Distribution of Fuel Sprays After Injection Cut-0ff (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: High-speed motion pictures were taken of fuel sprays with the NACA spray-photographic apparatus to study the distribution of the liquid fuel from the instant of injection cut-off until about 0.05 second later. The fuel was injected into a glass-walled chamber in which the air density was varied from 1 to 13 times atmospheric air density (0.0765 to 0.99 pound per cubic foot) and in which the air was at room temperature. The air in the chamber was set in motion by means of a fan, and was directed counter to the spray at velocities up to 27 feet per second. The injection pressure was varied from 2,000 to 6,000 pounds per square inch. A 0.20-inch single-orifice nozzle, an 0.008-inch single-orifice nozzle, a multiorifice nozzle, and an impinging-jets nozzle were used. The best distribution was obtained by the use of air and a high-dispersion nozzle.
    Materialart: NACA-TR-483
    Format: application/pdf
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  • 78
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    Working Charts for the Determination of Propeller Thrust at Various Air Speeds (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A set of propeller performance charts, based on a torque speed coefficient has been constructed from full-sized metal propeller data obtained in the NACA propeller-research tunnel.
    Materialart: NACA-TR-481
    Format: application/pdf
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  • 79
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    The Aerodynamic Effects of Wing Cut-Outs (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: In connection with the interference program being conducted in the NACA variable-density wind tunnel, an analysis was made of available material with the object of presenting a qualitative discussion on wing characteristics as affected by cut-outs and of determining means for their quantitative calculation.
    Materialart: NACA-TR-480
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  • 80
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    Effect of Viscosity on Fuel Leakage Between Lapped Plungers and Sleeves and on the Discharge from a Pump-Injection System (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Test data and analysis show that the rate of fuel leakage between a lapped plunger and sleeve varies directly with the density of the fuel, the diameter of the plunger, the pressure producing the leakage, and the cube of the mean clearance between the plunger and sleeve. The rate varies inversely as the length of the lapped fit and the viscosity of the fuel. With a mean clearance between the plunger and sleeve of 0.0001 inch the leakage amounts to approximately 0.2 percent of the fuel injected with gasoline and as low as 0.01 percent with diesel fuel oils. With this mean clearance an effective seal is obtained when the length of the lap is three times the diameter of the lap. The deformation of the sleeve and plunger under pressure is sufficient to change the rate of leakage appreciably from that which would be obtained if the clearance was constant under pressure.
    Materialart: NACA-TR-477
    Format: application/pdf
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  • 81
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    A Flight Investigation of the Lateral Control Characteristics of Short Wide Ailerons and Various Spoilers with Different Amounts of Wing Dihedral (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents the results of flight tests made to determine the lateral control characteristics of short wide ailerons and spoilers, as a consequence of the promise shown in wind-tunnel tests by these devices as means of obtaining lateral control, particularly at angles of attack above the stall. Several forms of spoilers, front-hinge, rear-hinge, plain retractable, and saw-tooth retractable were tested alone and in combination with the ailerons. The tests were made with several different amounts of wing dihedral so that the effect of the yawing moments of the different lateral control combinations, which varied from large negative to large positive values, could be evaluated. In conjunction with the tests, observations were made to throw some light on the feasibility of operating the airplane with two controls instead of the present three.
    Materialart: NACA-TR-494
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  • 82
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    An aerodynamic analysis of the autogiro rotor with a comparison between calculated and experimental results (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents an extension of the autogiro theory of Glauert and Lock in which the influence of a pitch varying with the blade radius is evaluated and methods of approximating the effect of blade tip losses and the influence of reversed velocities on the retreating blades are developed. A comparison of calculated and experimental results showed that most of the rotor characteristics could be calculated with reasonable accuracy, and that the type of induced flow assumed has a secondary effect upon the net rotor forces, although the flapping motion is influenced appreciably. An approximate evaluation of the effect of parasite drag on the rotor blades established the importance of including this factor in the analysis.
    Materialart: NACA-TR-487
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  • 83
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    AN APPLICATION OF THE VON KARMAN-MILLIKAN LAMINAR BOUNDARY-LAYER THEORY AND COMPARISON WITH EXPERIMENT (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-05-10
    Schlagwort(e): AIRCRAFT
    Materialart: NACA TN-544
    Format: application/pdf
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  • 84
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    The 1934 Contest for the Deutsch De La Meurthe Trophy (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents a description of the rules, history and new technical innovations in the Deutsch de la Meurthe Cup race of 1934.
    Materialart: NACA-TM-765
    Format: application/pdf
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  • 85
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    The interdependence of profile drag and lift with Joukowski type and related airfoils (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: On the basis of a systematic investigation of Gottingen wind-tunnel data on Joukowski type and related airfoils, it is shown in what manner the profile drag coefficient is dependent on the lift coefficient. The individual factors for the construction of the profile drag polars are given. They afford a more accurate calculation of the performance coefficients of airplane designs than otherwise attainable with the conventional assumption of constant drag coefficient.
    Materialart: NACA-TM-768
    Format: application/pdf
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  • 86
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    The Denis-gruson Six-component Wind-tunnel Balance (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The 6.C.1 balance is the first fully automatic balance assuring a continuous and simultaneous record of the aerodynamic characteristics of an airfoil in a wind tunnel. Because of the rapidity of the measurements a complete polar (six components) requires only about three minutes of wind, that is to say, of motive power, which is of interest for wind tunnels with high efficiency factors and may lead to the economical design of large size wind tunnels.
    Materialart: NACA-TM-772
    Format: application/pdf
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  • 87
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    Ground Effect on the Take-off and Landing of Airplanes (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Theories of ground effect and interference are explored as well as experimental methods to record the phenomenon. The consequences of the phenomenon on the airplane at take-off and landing are discussed.
    Materialart: NACA-TM-771
    Format: application/pdf
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  • 88
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    Total-head Meter with Small Sensitivity to Yaw (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The total-head meter is essentially a venturi, housing a pitot tube for obtaining the total head. In yaw the flow within the nozzle is deflected, depending upon the degree of yaw, to a greater or lesser extent into the axial direction of the nozzle. After experimenting with several nozzle forms as to their suitability, the best design was finally adopted. When, with the chosen nozzle form, the total head is 0.5 entrance section diameter downstream, the instrument supplies the genuine total head at low Reynolds Numbers up to 43 degrees yaw.
    Materialart: NACA-TM-775
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  • 89
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    A discussion of the several types of two-stroke-cycle engines (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report discusses different types of two-stroke engines as well as the three most important design factors: volume of scavenge and charge delivery, scavenging process (scavenging result), and result of charge. Some of the types of engines discussed include: single cylinder with crank-chamber scavenge pump and auxiliary suction piston linked to working connecting rod; and two cylinder engines with a rotary scavenge pump arrangement. Three and four cylinder engines are also discussed in various designs.
    Materialart: NACA-TM-776
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  • 90
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    Hydrodynamic Tests of Models of Seaplane Floats (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report contains the results of tank tests carried out at free trim on seventeen hulls and floats of various types. The data as to the weight on water, trim, and relative resistance for each model are plotted nondimensionally and are referenced both to the total weight and to the weight on water. Despite the fact that the experiments were not made systematically, a study of the models and of the test data permits nevertheless some general deductions regarding the forms of floats and their resistance. One specific conclusion is that the best models have a maximum relative resistance not exceeding 20 percent of the total weight.
    Materialart: NACA-TM-770
    Format: application/pdf
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  • 91
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    Tension Fields in Originally Curved, Thin Sheets During Shearing Stresses (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The analysis of the stresses in the sheet and stiffeners is predicated upon the direction of the wrinkles, particularly the tensile stresses (principal stresses). This analysis and the calculation of stresses after buckling form the subject of the present article. It includes: 1) metal cylinders with closely spaced longitudinal stiffeners; 2) metal cylinders with closely spaced transverse rings.
    Materialart: NACA-TM-774
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  • 92
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    The Drag of Airplane Wheels, Wheel Fairings, and Landing Gears - I (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report presents the results of tests made in the 7-by 10-foot wind tunnel and in the 20-foot tunnel of the National Advisory Committee for Aeronautics to determine the drag of a number of airplane wheels, wheel fairings, and landing gears designed or selected for an airplane of 3,000 pounds gross weight. All tests were made on full-size models; those in the 7-by 10-foot tunnel were made at air speeds up to 80 miles per hour and those in the 20-foot tunnel were made at air speeds up to 100 miles per hour. Although most of the landing-gear tests were made in conjunction with a fuselage and at 0 degree pitch angle, some of the tests were made in conjunction with fuselage plus wings and a radial air-cooled engine and at pitch angles from -5 degrees to 6 degrees to obtain an indication of the general effect of these various items on landing-gear drag. All tests were made in the absence of propeller slipstream.
    Materialart: NACA-TR-485
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  • 93
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    Experimental Verification of the Theory of Wind-Tunnel Boundary Interference (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The results of an experimental investigation on the boundary-correction factor are presented in this report. The values of the boundary-correction factor from the theory, which at the present time is virtually completed, are given in the report for all conventional types of tunnels. With the isolation of certain disturbing effects, the experimental boundary-correction factor was found to be in satisfactory agreement with the theoretically predicted values, thus verifying the soundness and sufficiency of the theoretical analysis. The establishment of a considerable velocity distortion, in the nature of a unique blocking effect, constitutes a principal result of the investigation.
    Materialart: NACA-TR-478
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  • 94
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    Combustion in a Bomb with a Fuel-Injection System (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Fuel injected into a spherical bomb filled with air at a desired density and temperature could be ignited with a spark a few thousandths of a second after injection, an interval comparable with the ignition lag in fuel-injection engines. The effect of several variables on the extent and rate of combustion was investigated: time intervals between injection and ignition of fuel of 0.003 to 0.06 second and one of 5 minutes; initial air temperatures of 100 degrees C. to 250 degrees C.; initial air densities equivalent to 5, 10, and 15 absolute atmospheres pressure at 100 degrees C.; and air-fuel ratios of 5 to 25.
    Materialart: NACA-TR-544
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  • 95
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    Tests of Nacelle-Propeller Combinations in Various Positions with Reference to Wings VI : Wings and Nacelles with Pusher Propeller (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report is the sixth of a series giving wind tunnel tests results on the interference drag and propulsive efficiency of nacelle-propeller-wing combinations. The present report gives the results of tests of a radial-engine nacelle with pusher propeller in 17 positions with reference to a Clark Y wing; tests of the same nacelle and propeller in three positions with reference to a thick wing; and tests of a body and pusher propeller with the thick wing, simulating the case of a propeller driven by an extension shaft from an engine within the wing. Some preliminary tests were made on pusher nacelles alone.
    Materialart: NACA-TR-507
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  • 96
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    A flight investigation of the effect of mass distribution and control setting on the spinning of the XN2Y-1 airplane (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The investigation of the effect of mass distribution on the spinning of airplanes initiated with tests on the NY-1 airplane has been continued by tests on another airplane in order to increase the scope of the information and to observe particularly the behavior of an airplane that shows considerable change in sideslip angle for its various conditions of spinning. The XN2Y-1 naval training biplane was used for the present tests in which changes of ballast along the longitudinal and lateral axes and changes of aileron, stabilizer, and elevator settings were made. The effects of these changes on the steady spin were measured in flight.
    Materialart: NACA-TR-484
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  • 97
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    Modification of wing-section shape to assure a predetermined change in pressure distribution (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: In order to find an airfoil for a predetermined pressure distribution, the problem must be posed so that the pressure distribution creates no drag. Another fundamental difficulty is that it is impossible to specify a pressure distribution without first knowing the place where these pressures are to be applied, i.e., the wing-section shape. This difficulty may be avoided by directing the pressure distribution along the contour of the wing section. Then it becomes possible to define the change in wing-section shape which effects a certain modification of the wing-section shape. The limitations underlying the required pressure distribution are discussed and it is found that the sole essential limitation is zero drag. The method is illustrated with an example.
    Materialart: NACA-TM-767
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 98
    facet.materialart.
    Unbekannt
    The bending of beams with thin tension flanges (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report analyzes the action of a cantilever T beam with a tension flange so thin it can only carry tensile stresses.
    Materialart: NACA-TM-769
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 99
    facet.materialart.
    Unbekannt
    Experiments with suction-type wings (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The present report collects the investigations of the past years which, while not as yet intended for use in construction, show different possibilities for the building of a suction-type wing and at the same time present some basic explanations concerning the problem of suction. Experiments and results with a thick wing profile are detailed as well as boundary layer removal by suction and sink action. Experiments with flap profiles are also included.
    Materialart: NACA-TM-773
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 100
    facet.materialart.
    Unbekannt
    Gliding in convection currents (1935)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A survey of the possibilities of gliding in convection currents reveals that heretofore only the most simple kind of ascending convection currents, that is, the "thermic" of insolation, has been utilized to any extent. With the increasing experience in gliding, the utilization of the peculiar nature of the "wind thermic" and increased glider speed promises further advances. Evening, ocean, and height "thermic" are still in the exploration stage, and therefore not amenable to survey in their effects.
    Materialart: NACA-TM-761
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
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