Accession Number : ADA319719
Title : Experimental Investigation of Supersonic Flows with Separated Regions in Ducts.
Descriptive Note : Final rept.,
Corporate Author : CENTRAL AERODYNAMIC INST MOSCOW (RUSSIA)
Personal Author(s) : Penzin, Viacheslav
PDF Url : ADA319719
Report Date : 30 SEP 1995
Pagination or Media Count : 238
Abstract : As applied to supersonic diffusers of different purpose and scramjet engines separation flows in various geometry ducts are investigated. Flow Mach and Reynolds numbers at the entrance to the ducts ranged from I to 6 and from 4.IO% to 7.1O%, respectively. The transition from supersonic flow to subsonic flow efficiency defined by the transition region length and pressure recovery. Separated and non- separated flow boundaries are determined. Hydraulic diameter concept expediency for separation flows analysis is appraised. Scramiet separation flows of different kinds were simulated. The influence on separation flows of such factors as off design modes of diffuser, combustors, non-uniformity of flow interaction of separated regions initiated by back pressure, secondary jets, cavities, struts and other kinds of elements of scramjet combustors are investigated. Several methods of separation control promoting flow stabilization and decreasing separated region lengths are offered.
Descriptors : *DUCTS, *SUPERSONIC FLOW, *SUPERSONIC COMBUSTION RAMJET ENGINES, STABILIZATION, DIAMETERS, RECOVERY, INTERACTIONS, EFFICIENCY, REGIONS, BOUNDARIES, LENGTH, GEOMETRY, SEPARATION, TRANSITIONS, MACH NUMBER, SUBSONIC FLOW, HYDRAULICS, FLOW SEPARATION, REYNOLDS NUMBER, BACK PRESSURE, DIFFUSERS, SUPERSONIC DIFFUSERS.
Subject Categories : Fluid Mechanics
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE