Aeroheating predictions for X-34 using an inviscid boundary-layer method

Radiative equilibrium surface temperatures and surface heating rates from a combined inviscid boundary-layer method are presented for the X-34 reusabl e launch vehicle for several points along the hypersonic descent portion of its trajectory. Inviscid, perfect-gas solutions are generated with the LAU RA and the DPLUR codes. Surface temperatures and heating rates are then com puted 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 m uch less computational effort than a Navier-Stokes code. This engineering m ethod enables the generation of a more thorough aerothermal database, which is necessary to design the thermal protection system and specify the vehic le's flight limits.