The use of Stokes stream function for axially symmetric prob¬lems in linearized supersonic flow is discussed. The computation of streamlines away from the body is shown to be facilitated by solving the stream-function problem rather than the potential prob¬lem. Use is made of the stream function throughout this report.nHalf-power supersonic source distributions along the axis of symmetry are shown to provide streamlines that, at finite distances from the axis, turn a sharp corner at the Mach cone and are regular downstream of the Mach cone. Distributions of this type are used to provide the following procedures for open-nosed bodies of revo¬lution at zero lift:n1. A numerical method for the computation of pressures along the body: The method, for which a simple example is given, is especially easy to apply on the forward part of the body.n2. Linearized formulas for the variation of strength and angle of the attached bow shock wave as functions of radial distance from the axis.
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