EFFECT ON BLUNTNESS ON HYPERSONIC TWO-DIMENSIONAL INLET TYPE FLOWS

摘要

An important aerodynamic phenomenon that warrants consideration in the development of inlet analytical techniques arises as a result of the practical constraint of leading edge bluntness. An investigation of the effect of bluntness on two-dimensional hypersonic inlet type flows has therefore been conducted. Specifically, tests were performed on two geometric configurations - a flat plate and an isentropic compression ramp - each accommodating leading edges of three different radii. The nominal test Mach numbers were 7.3 and 10.55, with corre¬sponding free-stream unit Reynolds number ranges of 0.25 to 2.0 x 106 per foot, and 0.75 to 2.0 x 106 per foot, respectively.nResults generated during the test phases of this program are compared with theoretical analyses and reflect blunt leading-edge effects on inviscid-flow profiles, surface-pressure phenomena and viscous-layer growth along the models, with and without incident shock wave-boundary layer interactions.