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  • Other Sources  (4)
  • NASA Technical Reports  (4)
  • Aircraft Design, Testing and Performance  (3)
  • Aerodynamics  (1)
  • 1930-1934  (4)
  • 1931  (4)
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  • Other Sources  (4)
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  • NASA Technical Reports  (4)
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  • 1930-1934  (4)
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  • 1
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    Wind Tunnel of the Bucharest Polytechnic Institute (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes the Bucharest wind tunnel and presents numerous photographs and diagrams. The wind tunnel is of the closed- circuit type, the return being symmetrical with respect t o the longitudinal axis of the tunnel. Th e tunnel is of the horizontal type with a diameter of 3. 2 m (10. 5-ft.) a t the beginning of the entrance cone, and 1.5 m ( 4,92 ft.) at the entrance to the test chamber. The latter, 2 m (6.56 ft.) long, may be either of the open-jet type or enclosed in a cylindrical housing.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-651
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    The Take-Off of Seaplanes, Based on a New Hydrodynamic Reduction Theory (1931)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The interpretation of the take-off resistance of seaplane floats by model test involves a problem in mechanics, the solution of which forms the basis of this report. The comparison of three float forms is confined to an angle = 5 degree trim run in order to preserve the clearness of the arrangement. But for complete comparison the corresponding curves for several trim runs should be included.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-621 , Zeitschrift fur Flugtechnik und Motorluftschiffahrt; 22; 8-12; 1
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Estimated Effect of Ring Cowl on the Climb and Ceiling of an Airplane, Special Report (1931)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Although the application of a ring cowl to an airplane with an air-cooled engine increases the maximum L/D and the high speed to an appreciable extent, the performance in climb and ceiling is not increased as much as one would expect without analyzing the conditions. When a ring cowl is installed on an airplane, the propeller is set at a higher pitch to allow the engine to turn its rated r.p.m. at the increased high speed. V/nD is increased and the propeller efficiency at high speed is increased slightly. The ratio of r.p.m. at climbing speed, V(sub c) , to the r.p.m. at maximum speed, V (sub m) is dependent upon the ratio of V(sub c) to V(sub m). The increase in V(sub c) for all airplane with ring cowl i s not as great as the increase in V(sub m), so that the ratio V(sub c)/V(sub m) is less than for the airplane without ring. Consequently the r.p.m. and full throttle thrust power available are less at V(sub c) for the airplane with ring cowl and in spite of the increase in L/D due to the installation of the ring, the excess thrust power available for climbing is not appreciably changed. The same method of reasoning accounts for the small increase in absolute ceiling in spite of a large increase in L/D maximum.
    Keywords: Aerodynamics
    Type: NACA-SR-3A , NACA Misc. Paper No. 26
    Format: application/pdf
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  • 4
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    Method of Determining the Weights of the Most Important Simple Girders (1931)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper presents a series of tables for the simple and more common types of girders, similar to the tables given in handbooks under the heading "Strength of Materials," for determining the moments, deflections, etc., of simple beams. Instead of the uniform cross section there assumed, the formulas given here apply only to girders of "uniform strength," i.e., it is assumed that a girder is so dimensioned that a given load subjects it to a uniform stress throughout its whole length. This principle is particularly applicable to very strong structures. Girders of uniform strength are the lightest girders conceivable, because any girder, all of whose members are stressed to the limit, can not be surpassed by a lighter girder, if the two girders have the same form. The weight G of a member of length l, cross section F and specific gravity gamma is: G = Flgamma.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-3B , Zeitschrift fur Flugtechnik und Motorluftechiffahrt (Magazine for Aeronautical Engineering and Motorluftechniffahrt); 22; 15; 456-463
    Format: application/pdf
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