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  • 1
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    Unknown
    Damping in Pitch and Roll of Triangular Wings at Supersonic Speeds (1948)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The expressions for the damping derivatives in pitch and roll of triangular wings are derived by means of the linearized theory. In the method used, the wing is represented by an unknown distribution of doublets. An integral equation containing the unknown distribution is set up and solved by analogy with known incompressible flow relations. It is pointed out that the results may be used to obtain damping coefficients of a limited series of sweptback wings, the most interesting of which are the so-called "arrow wings."
    Type: NACA-TN-1566
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Unknown
    Damping in Pitch and Roll of Triangular Wings at Supersonic Speeds (1948)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A method is derived for calculating the damping coefficients in pitch and roll for a series of triangular wings and a restricted series of sweptback wings at supersonic speeds. The elementary "supersonic source" solution of the linearized equation of motion is used to find the potential function of a line of doublets, and the flows are obtained by surface distributions of these doublet lines. The damping derivatives for triangular wings are found to be a function of the ratio of the tangent of the apex angle to the tangent of the Mach angle. As this ratio becomes equal to and greater than 1.0 for triangular wings, the damping derivatives, in pitch and in roll, become constant. The damping derivative in roll becomes equal to one-half the value calculated for an infinite rectangular wing, and the damping derivative in pitch for pitching about the apex becomes equal to 3.375 times that of an infinite rectangular wing.
    Type: NACA-TR-892
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    Determination of Shapes of Boattail Bodies of Revolution for Minimum Wave Drag (1951)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: By use of an approximate equation for the wave drag of slender bodies of revolution in a supersonic flow field, the optimum shapes of certain boattail bodies are determined for minimum wave drag. The properties of three specific families of bodies are determined, the first family consisting of bodies having a given length and base area and a contour passing through a prescribed point between the nose and base, the second family having fixed length, base area, and maximum area, and the third family having given length, volume, and base area. The method presented is easily generalized to determine minimum-wave-drag profile shapes which have contours that must pass through any prescribed number of points. According to linearized theory, the optimum profiles are found to have infinite slope at the nose but zero radius of curvature so that the bodies appear to have pointed noses, a zero slope at the body base, and no variation of wave drag with Mach number. For those bodies having a specified intermediate.diameter (that is, location and magnitude given), the maximum body diameter is shown to be larger, in general, than the specified diameter. It is also shown that, for bodies having a specified maximum diameter, the location of the maximum diameter is not arbitrary but is determined from the ratio of base diameter to maximum diameter.
    Keywords: unknown
    Type: NACA-TN-2550
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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