Experimental Verification of a Transonic Test Technique for Full-Scale Inlet/Engine Systems Simulating Maneuvering Attitudes
Final rept. 1 Jul 1973-30 Jun 1974
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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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.
- Jet and Gas Turbine Engines