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
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE