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    Cones in Supersonic Flow (1947)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: In the case of cones in axially symmetric flow of supersonic velocity, adiabatic compression takes place between shock wave and surface of the cone. Interpolation curves betwen shock polars and the surface are therefore necessary for the complete understanding of this type of flow. They are given in the present report by graphical-numerical integration of the differential equation for all cone angles and airspeeds.
    Keywords: Aerodynamics
    Type: NACA-TM-1157 , Jahrbuch 1942 der deutschen Luftfahrtforschung; 80-190
    Format: application/pdf
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