Three Dimensional Calculation of Hypersonic Flowfieldover Atmospheric Entry Body

摘要

A three-dimensional calculation of hypersonic flowfield over Apollo command module geometry is carried out, accounting for thermochemical nonequilibrium effects. From the calculated pressure distribution on the body surface aerodynamic coefficients are deduced and compared with that of the AS-202 flight data. A reasonable agreement for aerodynamic coefficients are obtained. Thermochemical nonequilibrium effects are shown to alter the aerodynamic coefficients considerably.