Abstract
Abstract : To solve the problem of a three-dimensional supersonic gas flow around three-dimensional bodies several effective computation schemes have been developed in recent years, which are based on the use of the finite difference method, the method of characteristics and the semi-characteristics method. Such numerical methods make it possible to determine with the required accuracy both the overall aerodynamic characteristics and the distribution of the various parameters on the surface of the body and across the shock layer. In these numerical computations it is also not difficult to account for physical-chemical processes occuring in the gas at high temperatures. (Author)
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