Reentry-f Flowweld Solutions at 80,000 Ft. Reentry-f Flowweld Solutions at 80,000 Ft

Three equilibrium-air numerical solutions are presented for the Reentry-F ight-test vehicle at Mach 20, 80,000 ft. conditions, including turbulent t o w predictions. The three solutions are from a thin-layer Navier-Stokes code, coupled thin-layer and parabolized Navier-Stokes codes, and an approximate viscous shock-layer code. Boundary-layer and shock-layer prooles are presented and compared between the three solutions, revealing close agreement between the three solution methods. Notable exceptions to the close agreement, with 7710 percent discrepancies, occur in the density prooles at the boundary-layer edge, in the boundary-layer velocity prooles, and in the shock-layer prooles in regions innuenced by the nose bluntness.