A base region heating analysis of the X-34 launch vehicle

The base region flow around the X-34 version 55B reusable launch vehicle is analyzed using a 3D reacting gas Navier-Stokes flow solver at two points along the vehicle's ascent trajectory. The radiative and convective heating to the engine compartment is computed. The maxiumum heating in the engine compartment is only 6.4 percent of the predicted maximum stagnation point heating at the vehicle nose during descent. There is no discernable recirculation of the nozzle exhaust gases into the engine compartment and no impingement of the nozzle exhaust gases on the aft control surfaces. (Author)