NONEQUILIBRIUM BOUNDARY-LAYER EFFECTS ON THE AERODYNAMIC HEATING OF HYPERSONIC WAVERIDER VEHICLES

The aerodynamic heating of hypersonic waverider vehicle configurations is examined in the high-altitude hypersonic flight regime where nonequilibrium dissociation-recombination in the boundary-layer and finite surface catalysis effects are both important. Analytical treatment of these effects is given for highly cooled surfaces in three important heating regions: 1) the nose, 2) the swept-wing leading-edge attachment line, and 3) the windward body centerline. Relationships for the relative nonequilibrium effects are developed for each region that enable both computer code-prediction validation and test-effective parametric engineering studies.