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The purpose of this work is to describe the suitable methods for aerodynamic characteristics calculation of hypersonic vehicles in free molecular flow and the transitional regimes. Moving of the hypersonic vehicles at high altitude, it is necessary to know the behavior of its aerodynamic characteristics for all flow regimes. Nowadays, various engineering approaches have been developed for modelling of aerodynamics of aircraft vehicle designs at initial state. The engineering method that described in this paper provides good results for the aerodynamic characteristics of various geometry designs of hypersonic vehicles in the transitional regime. In this paper present the calculation results of aerodynamic characteristics of various hypersonic vehicles in all range of regimes by using engineering method.

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The most significant problems of numerical schemes development, arising from specific problems of aeroacoustics are formulated. In this paper emphasized the necessity for the standard achievement, in which it is possible to test proposed scheme. The most reliable standard may be exact solution about propagation of sound in formulation approximate to consider the problem. In the work presents exact solution of acoustic radiation from two dimensional channels by Wiener-Hopf method.