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Direct Simulation Monte Carlo Method and Comparison
Drag of Bodies in Rarefied Hypersonic Flow
Heat Transfer on a Flat Plate in Continuum to Rarefied
19 other sections not shown
Aeroassisted Orbital Transfer AIAA Paper angle of attack AOTV approximately atom body boundary layer bow shock calculated Chemical Physics collision computed continuum contour convective correlation cross sections curve density dissociation downstream drag drag coefficient DSMC effect ELECTRON ENERGY enthalpy equations equilibrium experimental flat plate flight flowfield flux freestream gage heat transfer heat-transfer rate heating distributions heating rates Hypersonic Flow increase interaction inviscid Knudsen number laminar leading edge leeward heating Mach number mean free path measured method molecules Morse potential NASA nonequilibrium nosetip nozzle obtained Orbital Transfer Vehicles parameter particle predicted present pressure radiation radiative rate coefficients rate constants ratio re-entry reaction reattachment regime Reynolds number rotational scattering shock layer shock wave shown in Fig simulation solution stagnation point stagnation region strong interaction surface temperature theory thermal three-dimensional tion transition turbulent values velocity viscous wall wind tunnel windward centerline