Analysis of Ablation on Boundary Layer Stability of the Reentry F Flight Vehicle

Le résumé fourni par la source

View Video Presentation: https://doi.org/10.2514/6.2022-3775.vid Boundary layer stability at hypersonic speeds is sensitive to small flowfield changes. Nose tip ablation has multi-physical effects on the flow field that can potentially stabilize or destabilize the boundary layer by modifying the geometry, introducing additional chemical species, and changing the wall temperature profile. The objective of this work is to investigate how nonspherical nose tip blunting affects boundary layer stability for the Reentry F flight vehicle. A portion of the Reentry F flight experiment trajectory is simulated using a coupled fluid-solid solver which includes conjugate heat transfer (CHT) and gas-surface interaction (GSI) models. The resulting base flows with GSI modeled are used to compute a species mass flux of carbon from the nose tip, which is then used to determine an approximate recession rate as the flight vehicle descended from 100,000 ft (30.48 km) to 80,000 ft (24.38 km). A total recession distance is then computed and new grids are constructed for base flow computation and stability analysis. A sensitivity study of the effect of recession on boundary layer stability is then completed for 1x, 1.5x, and 2x the nominal recession using the parabolized stability equations (PSE). It is observed that this non-spherical blunting has strong destabilizing effects upstream of approximately 1 m, while the downstream boundary layer stability is unaffected.

Ce résumé expose les affirmations des auteurs. BNTIC ne l’interprète pas comme une validation indépendante des résultats.