Approximate method for calculation of laminar boundary layer with heat transfer on a cone at large angle of attack in supersonic flow

William E. Brunk
naca-tn-4380
Sep 1958


By the use of an integral technique, the laminar boundary-layer equations are reduced on the windward generator of the plane of symmetry to a set of simultaneous algebraic equations. The Chapman-Rubesin temperature-viscosity relation and a Prandtl number of 1 are assumed. The method enables the skin friction coefficients and Stanton number to be calculated in a much shorter time than was needed to obtain exact numerical solutions from the boundary-layer equations. The solutions obtained by this method are, for the most part, within 5 percentage points of the exact solutions.

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