Ysolde PREVEREAUD
DOI Number: 10.60853/ned6-7t19
Conference number: HiSST-2024-00247
An accurate determination of the wall heat flux in hypersonic regime is crucial for the design of any space vehicle and mission as well as to estimate space debris survivability. During vehicle pre-design and design phases, as well as space debris atmospheric entry calculation, analytical models are used to quickly estimate the wall heat flux. Existing models in the open literature are either applicable to specific flow conditions and/or only applicable to a limited number of shapes, and/or depend on local parameters not accessible by engineering approaches. Moreover, even when the models are used within their valid range, a high level of uncertainty is generally associated with the obtained solution. ONERA has been developing new surrogate models in hypersonic regime from rarefied to continuum flow conditions. The aim of the present paper is to present the very last formulations, developed to express stagnation point heat flux and 3D wall heat flux distribution in various flow regimes for any kind of shape.