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
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1958
- Accession Number
- AD0686441
Entities
People
- Anthony Casaccio
- Eugene Sevigny
- Marian Jr. Visich
- Paul A. Libby
- Robert J. Cresci
- Samuel Lederman
Organizations
- New York University Tandon School of Engineering