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  • 1
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    Effect of Aerodynamic Design on Glider Performance (1935)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: 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.
    Type: NACA-TM-762
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Method for the determination of the spanwise lift distribution (1935)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: 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.
    Type: NACA-TM-778
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    The Development, Design and Construction of Gliders and Sailplanes (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report explains and details the history of glider design and construction through the impetus of the Rhon Sailplane contests. Some of the topics considered include: whether the longitudinal stability (dynamic and static) is sufficient in the tailless typo and a consideration that the structural weight of sweptback wings would be greater than that of a corresponding normal wing.
    Type: NACA-TM-637
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Technical report of the 1928 Rhon soaring-flight contest (1929)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TM-514
    Format: application/pdf
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  • 5
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    Approximation method for determining the static stability of a monoplane glider (1927)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The calculations in this paper afford an approximate solution of the static stability. A derivation of the formulas for moment coefficient of a wing, moment coefficient of elevator, and the total moment of the combined wing and elevator and the moment coefficient with reference to the center of gravity are provided.
    Type: NACA-TM-436
    Format: application/pdf
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  • 6
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    Pressure Distribution Measurements at High Speed and Oblique Incidence of Flow (1947)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The present report contains the results of a series of observations obtained for a wing of symmetrical profile for different angles of yaw. The shock tunnel with 0.4m x 0.4m cross section, of the Institute for Gas Dynamics at L.F.A. - Braunchweig was available for this work. The profile used was a 9 percent, thick hyperbolic profile with maximum thickness 40 percent aft, which was calculated by the method of F. Ringleb (2). Since the conformal transformation of this profile is known, the theoretical pressure distribution could be determined exactly for the case of incompressible flow. Then by the use of the Prandtl rule one may extend the comparison of theory and experiment to the case of higher velocity of incident flow.
    Keywords: Aerodynamics
    Type: NACA-TM-1115 , Messerschmitt A.G.; 1669
    Format: application/pdf
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