A calculation of pressure recovery behind a normal shock in hypersonic flow

[摘要] An analytical model is devised for investigating the flow immediately behind the normal shock which stands in the throat of the conical shock diffuser of a hypersonic wind tunnel. A method is developed for calculating the flow properties, specifically the static and total pressures, for the case of large heat losses to the wall. An example is worked out to illustrate the method and some typical results.

[发布机构] Rice University