Accession Number:

AD0647761

Title:

NUMERICAL ANALYSIS OF THE BLUNT-TRAILING-EDGE SUPERSONIC COMPRESSOR,

Descriptive Note:

Corporate Author:

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

Personal Author(s):

• Olympios,Stavros

Report Date:

1966-09-01

Pagination or Media Count:

66.0

Abstract:

The report gives a detailed description of the IBM FORTRAN Program developed for prediction of the quasi-three-dimensional performance of blunt-trailing-edge supersonic rotor. The radial equilibrium equation is solved in the trailing-edge plane and after the abrupt area increase downstream of the rotor trailing edges. Two sample calculations are given one to illustrate a typical flow condition and one to illustrate the conditions existing when the blade passage is choked. Included also is a listing of the FORTRAN Program. Author

Descriptors:

• *SUPERSONIC CHARACTERISTICS
• TRAILING EDGES
• COMPRESSORS
• AXIAL FLOW COMPRESSORS
• BLUNT BODIES
• COMPRESSOR BLADES
• COMPRESSOR ROTORS
• DIFFUSION

Subject Categories:

• Hydraulic and Pneumatic Equipment
• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE