Abstract
THESE tables are prefaced by an account of the theory, which is based on work by Stone, hitherto unpublished. It is assumed that the motion is steady and isentropic along each streamline behind the shock wave, but not irrotational. The steady angle of yaw is taken to be a small quantity of the first order, and the equations for the first order perturbations of the known flow for zero yaw are worked out. Ultimately the solution is made to depend on a non-homogeneous ordinary differential equation of the second order. It appears that the shock wave is a circular cone the angle of yaw of which differs from that of the body.
Tables of Supersonic Flow Around Yawing Cones
By the Staff of the Computing Section, Center of Analysis, under the direction of Zdeněk Kopal. (Massachusetts Institute of Technology, Department of Electrical Engineering, Center of Analysis, Technical Report No. 3.) Pp. xviii + 321. (Cambridge, Mass. : Massachusetts Institute of Technology, 1947.) n.p.
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DUNCAN, W. Tables of Supersonic Flow Around Yawing Cones. Nature 162, 432 (1948). https://doi.org/10.1038/162432b0
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DOI: https://doi.org/10.1038/162432b0