| タイトル | Aerothermal Heating Predictions for Mars Microprobe |
| 本文（外部サイト） | http://hdl.handle.net/2060/20040087200 |
| 著者（英） | Mitcheltree, R. A.; Braun, R. D.; DiFulvio, M.; Horvath, T. J. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1998-01-01 |
| 言語 | eng |
| 内容記述 | A combination of computational predictions and experimental measurements of the aerothermal heating expected on the two Mars Microprobes during their entry to Mars are presented. The maximum, non-ablating, heating rate at the vehicle's stagnation point (at alpha = 0 degrees) is predicted for an undershoot trajectory to be 194 Watts per square centimeters with associated stagnation point pressure of 0.064 atm. Maximum stagnation point pressure occurs later during the undershoot trajectory and is 0.094 atm. From computations at seven overshoot-trajectory points, the maximum heat load expected at the stagnation point is near 8800 Joules per square centimeter. Heat rates and heat loads on the vehicle's afterbody are much lower than the forebody. At zero degree angle-of-attack, heating over much of the hemi-spherical afterbody is predicted to be less than 2 percent of the stagnation point value. Good qualitative agreement is demonstrated for forebody and afterbody heating between CFD calculations at Mars entry conditions and experimental thermographic phosphor measurements from the Langley 20-Inch Mach 6 Air Tunnel. A novel approach which incorporates six degree-of-freedom trajectory simulations to perform a statistical estimate of the effect of angle-of-attack, and other off-nominal conditions, on heating is included. |
| NASA分類 | Aerodynamics |
| レポートNO | AIAA Paper 98-0170 |
| 権利 | Copyright, Distribution under U.S. Government purpose rights |
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