Numerical analysis of chemically reacting inviscid flow in 2-D
During the reentry of spaceflight vehicles at an altitude of approximately 65 km the velocity of the vehicle is about 8 km/s in atmospheric air with a low density of about 10−4 kg/m 3. Moreover in this altitude the temperature and the pressure are 240 K and 10 Pa (at standard conditions the values of the density and pressure are approximately 1.22 kg/m 3 and 105 Pa, respectively). With a sound speed of 330 m/s we obtain a Mach number of 25 during this part of the reentry. The problem considered here is to calculate the shock position and flow properties for such hypersonic flight regimes. For this workshop we calculated the testcases 6.1.1, 6.1.3, 6.2.1 and 6.2.3.
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