Abstract
In this paper it is shown how to calculate the steady hypersonic inviscid flow, including a detached shock, around a blunt body. The steady flow is obtained as the limit for large time of time-dependent flow, starting with plane flow impinging on the body. The transient flow is the solution of a mixed initial-boundary-value problem for the partial differential equations of inviscid fluids which is solved by a difference scheme proposed by Lax and Wendroff. Our calculations show that by itself this difference scheme tends to be unstable and does not converge to the steady flow; by adding an artificial viscosity term we have succeeded in stabilizing the calculation. Section 4 is a fairly convincing theoretical explanation of this stabilizing effect and a new stability condition is derived. Both plane and cylindrical symmetries are considered; in the cylindrical case a variant of Richtmyer's [4] two-step version of the Lax-Wendroff difference scheme is used. This method, as does Richtmyer's, requires much fewer arithmetic operations as compared with the one-step method.
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