Abstract
AN establishment method is used for the numerical investigation of inviscid, thermally non-conducting gas flow in nozzles involving transonic velocities. The nozzle cross-section is elliptic or almost rectangular. The finite-difference scheme used to integrate the non-stationary equations of gas dynamics provides “through” computation of the flow region without isolating the shock waves or other singularities. The approximation errors due to replacing the differential by finite-difference equations are analyzed.
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