Multi-fidelity numerical study of heat augmentation on a hypersonic inflatable aerodynamic decelerator

We present a numerical investigation of the transitional flow and associated heat transfer augmentation experienced on the front of a hypersonic inflatable aerodynamic decelerator (HIAD) during atmospheric reentry. These simulations aim to replicate hypersonic wind-tunnel experiments conducted by Hollis (2018) for a scaled model geometry similar to the NASA Inflatable Reentry Vehicle Experiment (IRVE). The aerodynamic deflection experienced by a flexible sphere-cone aeroshell results in a large-scale roughness pattern following a scalloped axisymmetric shape, which induces earlier transition and increased heat transfer, affecting the design of the thermal protection system. We perform simulations at different freestream conditions of Mach number (M ≈ 6), Reynolds number (Re_∞ ≈ 7×10⁶ /m to 27×10⁶ /m), angle of attack (0° to 18°), and for varying scallop (roughness) heights. Results from Reynolds-averaged Navier-Stokes (RANS) simulations using different turbulence models, as well as wall-modeled large-eddy simulations (WMLES) will be presented.