Structure of the Shock Wave on Flat-Nose Power-Law Bodies

Abstract

Computations using the Direct Simulation Monte Carlo method are presented for hypersonic ∞ow over ∞at-nose power-law leading edges. The primary aim of this paper is to examine the geometry efiect of such leading edges on the shock wave structure. The impact of the nose-thickness and afterbody-shape variations on shock wave shape, shock standofi distance, and shock thickness of such leading edges is investigated by using a model that classifles the molecules in three distinct classes: \undisturbed freestream, \re∞ected from the boundary and \scattered, i.e., molecules that had been indirectly afiected by the presence of the leading edge. Comparisons based on shock wave standofi distance and shock wave thickness are made between these new blunt conflgurations and circular cylinder shape, usually assumed as the appropriate blunting geometry for heat transfer considerations. It was found that the new blunt leading edges provided smaller shock wave standofi distance and shock wave thickness, compared to the corresponding circular cylinder.