Accession Number:

AD0650134

Title:

A THEORETICAL ANALYSIS OF THE BLUNT-TRAILING-EDGE SUPERSONIC COMPRESSOR AND COMPARISON WITH EXPERIMENT,

Descriptive Note:

Corporate Author:

AEROSPACE RESEARCH LABS OFFICE OF AEROSPACE RESEARCH WRIGHT-PATTERSON AFB OHIO

Report Date:

1966-11-01

Pagination or Media Count:

91.0

Abstract:

The report describes the mathematical flow model developed for predicting the quasi-three dimensional performance of a blunt-trailing-edge supersonic rotor. A comparison of the theory with experiment is made. Some general performance trends are described and means by which performance might be improved are considered. Finally, the blunt-trailing-edge design philosophy is discussed by considering the effects of the blade geometric parameters on the overall rotor performance. It was concluded that the flow model is adequate to predict mass-average performance. However, further refinements are necessary in order to predict the measured radial distributions downstream of the rotor. Author

Subject Categories:

  • Hydraulic and Pneumatic Equipment
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE