Abstract
Supersonic laminar flow past a sphere and a cylinder placed perpendicular to the freestream is investigated on the basis of the numerical solution of the Navier—Stokes equations. The gas is assumed to be perfect, with a constant specific heat ratio, and the surface temperature is fixed and taken to be the same as to the recovery temperature. The calculations are carried out at the Mach number 3 (cylinder) and 5 (sphere) in the Reynolds number range from 1 to 3000. The effect of the boundary slip and no-slip conditions imposed on the body surface on the flow parameters is investigated. Emphasis is placed on the determination of the aerodynamic characteristics. The results obtained are compared with the available experimental and calculated data.
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