Accession Number:

AD0787659

Title:

Experimental Verification of a Transonic Test Technique for Full-Scale Inlet/Engine Systems Simulating Maneuvering Attitudes

Descriptive Note:

Final rept. 1 Jul 1973-30 Jun 1974

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

Report Date:

1974-10-01

Pagination or Media Count:

36.0

Abstract:

An experimental investigation was conducted to demonstrate the capability of a newly developed flow-shaping technique to test full-scale inlet engine systems in the AEDC 16-ft Propulsion Wind Tunnel transonic at angles of yaw and combinations of angle of attack and yaw. Simulation of the flow field approaching the inlet was accomplished at Mach numbers in the range from 0.6 to 0.9 at positive yaw angles up to 6 deg over an angle-of-attack range from 0 to 8 deg and at negative yaw angles up to 6 deg over an angle of attack range from 0 to 12 deg. Inlet pressure distribution ramp, lip, and sideplate, local flow angularity, and local Mach number in front of the inlet were used to verify the technique.

Subject Categories:

  • Aerodynamics
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE