Maneuvering Aerothermal Technology (MAT) Program. A Method for Coupled Three-Dimensional Inviscid and Integral Boundary Layer Calculations.

摘要

A procedure is developed for computing the complete flow field over maneuvering reentry vehicles by coupling a finite difference inviscid flow field code to an integral boundary layer procedure. Viscous calculations are performed along inviscid surface streamlines, which are explicitly computed in the inviscid code. The detailed inviscid flow field solution is used to accurately define the required boundary layer edge properties. The boundary layer procedure can treat laminar, transitional, or turbulent flows, and surface roughness and mass addition effects. Approximate techniques are provided to define the wall temperatures and mass addition rates of ablating heatshields. (Author)