Accession Number : ADA181257
Title : Unsteady Flow in Supersonic Inlet Diffusers.
Descriptive Note : Final technical rept.,
Corporate Author : MICHIGAN UNIV ANN ARBOR COLL OF ENGINEERING
Personal Author(s) : Adamson,T C , Jr ; Messiter,A F
PDF Url : ADA181257
Report Date : Dec 1986
Pagination or Media Count : 9
Abstract : A symmetric supersonic inlet diffuser with flow at supercritical conditions has been analyzed, using both analytical and numerical methods. An equation describing the unsteady motion of the shock passage caused by vibrations in back pressure and/or variations in wall shape has been derived for inviscid flow. Results have been compared with those found using numerical methods both for inviscid and viscous flows fields. Keywords: Inlet flows; Unsteady inlet flows; Diffusers.
Descriptors : *SUPERCRITICAL FLOW, *SUPERSONIC DIFFUSERS, *SUPERSONIC INLETS, NUMERICAL METHODS AND PROCEDURES, INVISCID FLOW, SYMMETRY, VISCOUS FLOW, BACK PRESSURE, EQUATIONS, FLOW, INLETS, UNSTEADY FLOW, VIBRATION, SHAPE, WALLS
Subject Categories : Aircraft
Distribution Statement : APPROVED FOR PUBLIC RELEASE