Hypersonic boundary layer transition for X-33 Phase II vehicle

Abstract

A status review of the experimental and computational work performed to support the X-33 program in the area of hypersonic boundary-layer transition is presented. Global transition fronts are visualized using thermographic phospor measurements. Results are used to derive transition correlations for smooth body and discrete roughness models and a computational tool is developed to predict transition onset for X-33 using these correlations. The X-33 thermal protection system appears to be conservatively designed based on these models. Additional study is needed to address concerns related to surface waviness before final conclusions can be made. A discussion of future test plans is included.