Accession Number : ADP000260
Title : Evolution of Shock-Induced Pressure on a Flat-Face/Flat-Base Body and Afterbody Flow Separation,
Corporate Author : NATIONAL AERONUATICS AND SPACE ADMINISTRATION MOFFETT FIELD CA AMES RESEARCH CENTER
Personal Author(s) : Yoshikawa,Kenneth K. ; Wray,Alan A.
Report Date : JUL 1981
Pagination or Media Count : 9
Abstract : The time-dependent, compressible Reynolds-averaged, Navier-Stokes equations are applied to solve an axisymmetric supersonic flow around a flat-face/flat-base body with and without a sting support. Important transient phenomena, not yet well understood, are investigated, and the significance of the present solution to the phenomena is discussed. The phenomena, described in detail, are as follows: the transient formation of the bow and recompression shock waves; the evolution of a pressure buildup due to diffraction of the incident shock wave in the forebody and afterbody regions, including the luminosity accompanying the pressure buildup; the separation of the flow as influenced by pressure buildup; the location of the separation and the reattachment points; and the transient period of the shock-induced base flow. The important influence of the nonsteady (transient) and steady flow on the aerodynamic characteristics, radiative heat transfer, and, thus, on the survivability of safeguard problems for an aircraft fuselage, missile, or planetary entry probe at very high flight speeds is described.
Descriptors : *Flow separation, *Flat plate models, *Afterbodies, *Shock waves, *Pressure, Bow shock, Peak values, Pressure, Navier stokes equations
Distribution Statement : APPROVED FOR PUBLIC RELEASE