Accession Number : AD0686441

Title :   THEORETICAL AND EXPERIMENTAL INVESTIGATION OF A HYPERSONIC MULTI-STAGE COMPRESSOR. PART I. AERODYNAMIC STUDY OF THE COMPRESSOR PERFORMANCE. PART II. PRELIMINARY ANALYSIS OF THE HEAT TRANSFER TO THE COMPRESSOR BLADES,

Corporate Author : POLYTECHNIC INST OF BROOKLYN N Y DEPT OF AEROSPACE ENGINEERING AND APPLIED MECHANICS

Personal Author(s) : Sevigny,Eugene ; Visich,Marian , Jr. ; Cresci,Robert J. ; Casaccio,Anthony ; Lederman,Samuel

Report Date : DEC 1958

Pagination or Media Count : 27

Abstract : In order to determine further the feasibility of using a supersonic compressor as a source of high stagnation temperature air for hypersonic wind tunnel testing, a detailed aerodynamic study was made of a four-stage counter-rotating supersonic compressor. The performance of the compressor was calculated assuming that the relative Mach number entering and leaving the rotor was the same and, therefore, the flow was only turned in the rotor. (Author)

Descriptors :   (*HYPERSONIC WIND TUNNELS, COMPRESSORS), FEASIBILITY STUDIES, GAS FLOW, VELOCITY, COMPRESSOR BLADES, STAGNATION POINT, THERMAL STABILITY, HIGH TEMPERATURE

Subject Categories : Hydraulic and Pneumatic Equipment
      Test Facilities, Equipment and Methods

Distribution Statement : APPROVED FOR PUBLIC RELEASE