Abstract:
An analytical description is given to the solution of gas-dynamic equations corresponding to two-dimensional steady gas flow involving an oblique shock. For this flow, two limiting asymptotic regimes are possible: a decelerating supersonic flow regime and a flow regime accelerating to maximum horizontal velocity. A shock solution corresponds to switching over between integral curves of the governing equation. In the case of an extremely strong shock wave, the shock becomes limiting and rotates the flow through the maximum possible angle (for an adiabatic exponent equal to three). The shock-wave structure proposed is general for a broad class of nonbarochronic, regular, partially invariant solutions of the equations of gas dynamics.
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