Abstract
An experimental study of the hypersonic rarefied gas flow over a flat plate with a sharp leading edge is presented. Experiments in a low-density wind tunnel using an electron beam probe were conducted at the Shock Wave Laboratory, RWTH Aachen, Germany. Rotational temperatures for stagnation temperatures of To = 670 ∼ 1000 K and Kn = 0.024 ∼ 0.028 based on a reference length of 0.05 m were calculated by Muntz's method and by Robben and Talbot's method. The domain of quasi-two-dimensional flow over the plate was determined from three-dimensional rotational temperature measurements. A direct simulation Monte Carlo (DSMC) method is applied to obtain a nonequilibrium state for the rarefied gas flow over the flat plate.
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