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Dsmc simulations of orex entry conditions
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Moss, James N. Gupta, Roop N. Price, Joseph M. |
| Copyright Year | 1996 |
| Description | 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. |
| File Size | 371360 |
| Page Count | 6 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19960042539 |
| Archival Resource Key | ark:/13960/t0vq7vx6s |
| Language | English |
| Publisher Date | 1996-08-24 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Design, Testing And Performance Earth Atmosphere Aerothermochemistry Reentry Vehicles Stagnation Point Computerized Simulation Space Flight Monte Carlo Method Pressure Japanese Spacecraft Reentry Effects Spacecraft Trajectories Reentry Physics Aerodynamic Heating Acceleration Physics Flight Simulation Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
