Results are provided from a viscous shock layer (VSL) analysis of the reentry flowfield around the forebody of the Japanese Orbital Reentry Experiment (OREX) vehicle. This vehicle is a 50 deg. spherically blunted cone with a nose radius of 1.35 m and a base diameter of 3.4 m. Calculations are done for the OREX trajectory from 105 to 48.4 km altitude range. A 7-species chemical model is found adequate for the flowfield analysis. However, for altitudes greater than 84 km, the low density effects (such as thermal nonequilibrium and slip) are to be implemented for good agreement between the predictions and flight inferred heat-transfer rate data. Overall, there is a good comparison between the flight data and calculated results.
Assessment of Thermochemical Nonequilibrium and Slip Effects for Orbital Reentry Experiment (OREX)
1996
20 pages
Report
Keine Angabe
Englisch
Unmanned Spacecraft , Spacecraft Trajectories & Flight Mechanics , Forebodies , Heat transfer , Reentry effects , Reentry vehicles , Thermochemistry , Computerized simulation , Flow distribution , High altitude , Japanese space program , Mathematical models , Monte carlo method , Shock layers , Trajectories
Assessment of Thermochemical Nonequilibrium and Slip Effects for Orbital Reentry Experiment (OREX)
British Library Conference Proceedings | 1996
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TIBKAT | 1995
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