Direct simulation Monte Carlo calculations of aerothermodynamics for Mars Microprobe capsules

The hypersonic transitional flow aerodynamics of the Mars Microprobe capsul es are simulated with the direct simulation Monte Carlo method. Calculation s of axial, normal, and static pitching coefficients were obtained over an angle of attack range comparable to actual Eight requirements. Comparisons are made with modified Newtonian and free-molecular flow calculations. Aero thermal results were also obtained for zero incidence entry conditions. The current aerodynamic results are shown to be in excellent agreement with Na vier-Stokes results for small Knudsen number conditions. Peak heating condi tions occur under rarefied conditions where the heating becomes a strong fu nction of assumptions concerning surface catalytic activity.