CONSTRUCTION OF CONFIGURATION FOR A BODY WITH HIGH LIFT-DRAG RATIO MINIMIZING THE HEAT FLUX TO ITS SIDE SURFACE

High supersonic gas flow is characterized by high heat content (enthalpy) and high heat flux to a body surface; this should be remembered during construction of an optimal body shape. In particular, the mandatory requirement on optimal configuration in high-enthalpy supersonic flow is bluntness of nose and leading edges. Bluntness shape of axisymmetric and flat bodies of minimal drag is studied in [1-3], which results can be used for determining a shape of blunted nose and leading edges of three-dimensional configurations. The body shape of maximal lift-drag ratio (LDR) in hypersonic flow is studied in details [4], and the results obtained do not include heat application to a surface of such body. A problem on limitation of heat flux to a body surface can be formulated as determination of a body shape, which either minimize heat flux at given LDR value K or realizing maximal LDR at given heat flux. Algorithms for calculating force and heat loads that are used in course of computations should be both sufficiently simple for numerical realization and simulate correctly the real physical processes in high temperature gas flow. In this connection the tangent wedge method is used below for determining the force loading, and simulation of heat loading is going using the Reynolds analogy, which validity will be discussed by the example of a flow around a delta wing.