Abstract
The development of supersonic aircrafts should rely on advanced methods of flow control in order to improve the efficiency and reliability of the aircrafts. This article presents numerical simulation of energy supply to the incoming flow and simulation of the flow over bodies with hemispherical and conical nose parts. The numerical study was based on the model of an inviscid perfect gas described by the Euler equations which were solved by using the explicit unsteady Godunov’s numerical scheme with the second-order accuracy.
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