Results of direct simulation Monte Carlo (DSMC) solutions are presented for the Japanese Orbital Reentry Experiment (OREX) vehicle, a 50 deg half-angle spherically blunted cone with a nose radius of 1.35 m and a base diameter of 3.4 m. The flow conditions simulated are those for entry into the Earth's atmosphere at a nominal velocity of about 7.4 km/s and zero incidence. Calculations are made for the higher altitude portion of entry, encompassing the transitional flow regime (altitudes of 200 to 80 km). Comparisons with flight measured values are made for axial acceleration, surface pressure, and stagnation point heating.
DSMC Simulations of Orex Entry Conditions
1996
6 pages
Report
No indication
English
Spacecraft Trajectories & Flight Mechanics , Acceleration (Physics) , Aerodynamic heating , Computerized simulation , Flight simulation , Monte carlo method , Pressure , Reentry effects , Reentry vehicles , Space flight , Aerothermochemistry , Earth atmosphere , Japanese spacecraft , Reentry physics , Spacecraft trajectories , Stagnation point
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