FLOW IN SHOCK LAYER
Determination of Flow Field in a Nonequilibrium Shock Layer
An approximate inverse solution is presented for the nonequilibrium flow in the inviscid shock layer about a vehicle in hypersonic flight. The method is based upon a thin-shock-layer approximation and has the advantage of being applicable to both subsonic and supersonic regions of the shock layer. The relative simplicity of the method allows for a significant reduction in storage capacity and computing time. Additional cases are presented for entry of spherical nose cones into representative Venusian and Matrian atmospheres. A digital computer program written in FORTRAN language is presented that permits an arbitrary gas mixture to be employed in the solution. The effects of vibration, dissociation, recombination, electronic excitation, and ionization are included in the program.
Program Size: 3,000 Statements
Computer Language: FORTRAN IV
Copyright (c) 1996 Pacific HiTech, Inc. and COSMIC 
