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  • Other Sources  (13)
  • 1925-1929
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  • 1
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    Über die Temperaturabhängigkeiten von Insekten. 1. Über die Vorzugstemperatur einiger Insekten (1928)
    In:  Zeitschr. wiss. Biol. Abt. C. Vergl. Physiol. 8; p.1-16
    Details
    Publication Date: 1928
    Description: Der Autor beschreibt Laborversuche zur Ermittlung der Vorzugstemperatur von Tribolium confusum, Rhizoperta dominica, Capnodis carbonaria, Scanthius aegyptius und weiteren Insekten mit Hilfe einer Temperaturorgel. Die Insekten wurden dabei zudem noch unterschiedlichen Vorbehandlungen unterzogen. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Labor ; 1926-28
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    BIBLIOGRAPHY INKA BB
  • 2
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    Viscosity of diesel engine fuel oil under pressure (1929)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In the development of Diesel engine fuel injection systems it is necessary to have an approximate knowledge of the absolute viscosity of the fuel oil under high hydrostatic pressures. This report presents the results of experimental tests conducted by Mr. Jackson Newton Shore, utilizing the A.S.M.E. high pressure equipment.
    Type: NACA-TN-315
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Strength of tubing under combined axial and transverse loading (1929)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-307
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Effect of Variation of Chord and Span of Ailerons on Rolling and Yawing Moments in Level Flight (1929)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of an 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 wing sections. Some attention is devoted to a study of the effect of scale on rolling and yawing moments and to the effect of slightly rounding the wing tips. The results apply to level flight with the wing chord set at an angle of attack of +4 degrees and to conditions of zero pitch, zero yaw, and zero roll of the airplane. It is planned later to extend the investigation to other attitudes for monoplane and biplane combinations. The work was conducted in the 10 foot wind tunnel of the Bureau of Standards on models of 60-inch span and 10-inch chord. (author)
    Type: NACA-TR-298
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    The Direct Measurement of Engine Power on an Airplane in Flight with a Hub Type Dynamometer (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes tests made to obtain direct measurements of engine power in flight. Tests were made with a Bendemann hub dynamometer installed on a modified DH-4 Airplane, Liberty 12 Engine, to determine the suitability of this apparatus. This dynamometer unit, which was designed specially for use with a liberty 12 engine, is a special propeller hub in which is incorporated a system of pistons and cylinders interposed between the propeller and the engine crankshaft. The torque and thrust forces are balanced by fluid pressures, which are recorded by instruments in the cockpit. These tests have shown the suitability of this type of hub dynamometer for measurement of power in flight and for the determination of the torque and power coefficients of the propeller. (author)
    Type: NACA-TR-252
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Flame Speed and Spark Intensity (1925)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes a series of experiments undertaken to determine whether or not the electrical characteristics of the igniting spark have any effect on the rapidity of flame spread in the explosive gas mixtures which it ignites. The results show very clearly that no such effect exists. The flame velocity in carbon-monoxide oxygen, acetylene oxygen, and gasoline-air mixtures was found to be unaffected by changes in spark intensity from sparks which were barely able to ignite the mixture up to intense condenser discharge sparks having fifty time this energy. (author)
    Type: NACA-TR-187
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    The variation in engine power with altitude determined from measurements in flight with a hub dynamometer (1929)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The rate of change in power of aircraft engines with altitude has been the subject of considerable discussion. Only a small amount of data from direct measurements of the power delivered by airplane engines during flight, however, has been published. This report presents the results of direct measurements of the power delivered by a Liberty 12 airplane engine taken with a hub dynamometer at standard altitudes from zero to 13,000 feet. Six flights were made with the engine installed in a modified DH-4 airplane. The experimental relation of brake horsepower to altitude is compared with two theoretical relations and with the experimental results, for a second Liberty 12 engine, given in NACA Technical Report no. 252. The rate of change in power with altitude of a third Liberty engine, measured with a calibrated propeller, is also given for comparison. The data presented substantiate the theoretical relation of brake horsepower to altitude based on the correction of ground level indicated horsepower for change in atmospheric temperature and pressure with the subsequent deduction of friction horsepower corrected for altitude. (author)
    Type: NACA-TR-295
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Electrical characteristics of spark generators for automotive ignition (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper reports the results of an extensive program of measurements on 11 ignition systems differing widely in type. The results serve primarily to give representative data on the electric and magnetic constants of such systems, and on the secondary voltage produced by them under various conditions of speed, timing, shunting resistance, etc. They also serve to confirm certain of the theoretical formulas which have been proposed to connect the performance of such systems with their electrical constants, and to indicate the extent to which certain simplified model circuits duplicate the performance of the actual apparatus.
    Type: NACA-TR-241
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Some aspects of the comparison of model and full-scale tests (1926)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper was delivered before the Royal Aeronautical Society as the 1925 Wilbur Wright Memorial lecture. It treats the subject of scale effect from the standpoint of the engineer rather than the physicist, in that it shows what compromises are necessary to secure satisfactory engineering model test data and how these test data compare with full scale or with theoretical values. The paper consists essentially of three parts: (1) a brief exposition of the theory of dynamic similarity, (2) application of the theory to airplane model tests, illustrated by test data on airfoils from the National Advisory Committee for Aeronautics variable-density wind tunnel, and (3) application of the theory to propeller testing, illustrated by comparisons of model and full-scale results.
    Type: NACA-TR-219
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Some impressions of the Paris Aero Show (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TM-407
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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