Experimental Verification of a Transonic Test Technique for Full-Scale Inlet/Engine Systems Simulating Maneuvering Attitudes
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1974
- Accession Number
- AD0787659
Entities
People
- R. L. Palko
Organizations
- Arnold Engineering Development Complex