Abstract
Three-dimensional calculations are carried out to clarify the effect of high temperature real-gas phenomena on the aerodynamic characteristics of Mars aeroshell geometry. The calculated aerodynamic coefficients are compared with the experimental date obtained in the hypersonic wind tunnel test. Under the frozen flow assumption, the calculated aerodynamic coefficients agree well with the experimental data. The results in the nonequilibrium calculation show that the real gas effects alter the position of recompression zone in the shock layer, consequently the aerodynamic coefficients of the aeroshell.
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