Results of a numerical study using the direct simulation Monte Carlo (DSMC) method are presented for hypersonic rarefied flow over an aeroassisted space transfer vehicle (ASTV). The emphasis of the study is the characterization of the near wake region which includes the ASTV payload. The study covered the transitional flow regime from near continuum to free molecular. Calculations show that the character of the near wake is significantly affected by the presence of the payload. Flow separation occurs when an afterbody is present throughout the transitional flow regime. In contrast, when no afterbody is present, no separation is observed until the flow approaches continuum.
Hypersonic Rarefied Wake Characterization
1993
25 pages
Report
No indication
English
Fluid Mechanics , Spacecraft Trajectories & Flight Mechanics , Afterbodies , Computational fluid dynamics , Hypersonic flow , Monte carlo method , Near wakes , Rarefied gas dynamics , Separated flow , Transition flow , Aeroassist , Boundary layer separation , Characterization , Orbit transfer vehicles , Payloads
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