Aeroheating Predictions for X-34 Using an Inviscid Boundary-Layer Method

Abstract

Radiative equilibrium surface temperatures and surface heating rates from a combined inviscid-boundary layer method are presented for the X-34 Reusable Launch V ehicle for several points along the hypersonic descent portion of its trajectory. I n viscid, perfect-gas solutions are generated with the Langley Aerothermodynamic Upwind Relaxation Algorithm LAURA and the Data-Parallel Lower-Upper Relaxation DPLUR code. Surface temperatures and heating rates are then computed using the Langley Approximate Three-Dimensional Convective Heating LATCH engineering code employing both laminar and turbulent ow models. The combined inviscid-boundary layer method provides accurate predictions of surface temperatures over most of the vehicle and requires much less computational e ort than a Navier-Stokes code. This enables the generation of a more thorough aerothermal database which is necessary to design the thermal protection system and specify the vehicle's ight limits. Research Engineer, Aerothermodynamics Branch, Aeroand Gas-Dynamics Division. Senior Member AIAA.

Computational Aeroheating Predictions for X-34

“…(An additional case that does not include the aft portion of the vehicle is also presented.) Riley et al, 12 anchoredto these results,expandedthe trajectory envelope using a coupled, inviscid boundary-layer method. Incorporating the data from this limited array of trajectory points, Wurster et al 14 developed a time history of heating rates for the entire trajectory using engineeringcodes.…”

Aeroelastic analysis of hypersonic vehicles

“…In another reference (Gupta et al, 2001), CFD-based flutter analysis was used for the aeroelastic analysis of the X-43 configuration, using system identificationbased order reduction of the aerodynamic degrees of freedom. Both the structure and the fluid were discretized using From the studies on various hypersonic vehicles (Ricketts et al, 1993;Berry et al, 1999;Riley and Alter, 1998;Gupta et al, 2001) one can identify operating envelopes for each vehicle. A graphical representation of these operating conditions is shown in Fig.…”

Three-dimensional Aeroelastic and Aerothermoelastic Behavior in Hypersonic Flow

“…From the studies on previous hypersonic vehicles, 11,19,22,23 one can identify operating envelopes for each vehicle. A graphical representation of these operating conditions is shown in Fig.…”