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DSMC simulations of OREX entry conditionsResults 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.
Document ID
19960042539
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Moss, James N. (NASA Langley Research Center Hampton, VA United States)
Gupta, Roop N. (NASA Langley Research Center Hampton, VA United States)
Price, Joseph M. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
August 24, 1996
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NAS 1.15:111621
NASA-TM-111621
Report Number: NAS 1.15:111621
Report Number: NASA-TM-111621
Meeting Information
Meeting: International Symposium on Rarefied Gas Dynamics
Location: Beijing
Country: China
Start Date: August 19, 1996
End Date: August 24, 1996
Accession Number
96N31519
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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