Aeroheating Predictions for X-34 Using an Inviscid Boundary-Layer Method
- 1 March 1999
- journal article
- research article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in Journal of Spacecraft and Rockets
- Vol. 36 (2) , 206-215
- https://doi.org/10.2514/2.3451
Abstract
Radiative equilibrium surface temperatures and surface heating rates from a combined inviscid boundary-layer method are presented for the X-34 reusable launch vehicle for several points along the hypersonic descent portion of its trajectory. Inviscid, perfect-gas solutions are generated with the LAURA and the DPLUR codes. Surface temperatures and heating rates are then computed using the LATCH engineering code employing both laminar and turbulent Row models. The combined inviscid boundary-layer method provides accurate predictions of surface temperatures over most of the vehicle and requires much less computational effort than a Navier-Stokes code. This engineering method enables the generation of a more thorough aerothermal database, which is necessary to design the thermal protection system and specify the vehicle's flight limits.Keywords
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