Computation of Supersonic Turbulent Flows over an Inclined Ogive-Cylinder-Flare

A supersonic turbulent flow over an ogive-cylinder-flare has been solved numerically. The calculations proceed in two parts. Initially, the parabolized Navier-Stokes equations are solved for the ogive cylinder back to a location upstream of the shock-wave and boundary-layer interaction. Then, the time-dependent Navier-Stokes equations with a thin-layer approximation are solved for the remaining cylinder-flare portion. Results for a Mach number of 2.0 and a unit Reynolds number of 11.42 x 10(exp 6)/m are obtained for angles of attack alpha = 0, 4, and 8 deg. Good agreement has been found between computed and experimental results of the surface pressure on the ogive-cylinder portion and for the interaction region at alpha = 0 and 4 deg. The role of circumferential communication in a three-dimensional shock-wave and boundary-layer interaction flowfield is discussed.