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

摘要

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 0.6to 0.9at positive yaw angles up to 6deg over an angle-of-attack range from 0to 8deg and at negative yaw angles up to 6deg over an angle of attack range from 0to 12deg. 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. (Modified author abstract)