Abstract
Heat transfer in the region of the leading edge of a hypersonic flying vehicle has been calculated by finite‐difference integration of the Reynolds equations closed by the low‐Reynolds version of the k–e model of turbulence. Integration has been performed using the explicit–implicit McCormack scheme. It is shown that blowing of a cooling agent through a porous insert can lead to a substantial decrease of heat flux. The Darcy equation was used in solution of the conjugate problem.
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