Cross-flow transition model predictions of hypersonic transition research vehicle

Abstract

Hypersonic transition research vehicle (HyTRV) is a customized lifting body for studying hypersonic three-dimensional boundary-layer transition on a complex geometry. In this study, the transition model of an HyTRV lifting body at relatively high angles of attacks is investigated. A hypersonic cross-flow transition correlation is embedded in the γ-Re˜θt transition model on the Chant2.0 computing platform, called the C-γ-Reθ transition model. The transition model is validated in a series of typical three-dimensional aerodynamic configurations. HyTRV's flow characteristics and transition phenomenon are investigated. The model predictions are in good agreement with the stability analysis results and shockwave wind tunnel flow visualizations, exhibiting the model potential for hypersonic cross-flow transition prediction. The results of wind tunnel experiments, stability analysis, and model predictions confirm that transition regions on the upper/lower surface of HyTRV are dominated by cross-flow instabilities. With an increase in the angle of attack, the circumferential pressure gradient on the lower surface decreases and cross-flow intensity reduces; the transition onset location recesses until finally disappears. 2–3 pairs of isolated cross-flow transition zones exist on the surface of the HyTRV at a low angle of attack, which guarantees the HyTRV to be a typical validation case for cross-flow transition modeling.