Numerical and experimental investigation of the reduction of hypersonic nose tip ablation

Abstract

To reduce the severe heating and ablation at the nose tip of a hypersonic vehicle, the introduction of a forward-facing cavity into the nose tip is explored. In the present joint numerical/experimental study, the effects of the cavity on ablation are explicitly addressed whereas previous studies have concentrated on heating rates alone. While the study is continuing, initial results look promising. Numerical and experimental results agree surprisingly well for a baseline hemisphere cylinder case.