Experimental Verification of a Technique for Testing Full-Scale Inlet/ Engine Systems at Angles of Attack up to 20 Deg at Transonic Speeds
Abstract
A study was conducted to demonstrate experimentally the capability of a new flow-shaping technique to extend the full-scale inlet/engine testing limit of the AEDC 16-Ft Transonic Wind Tunnel. Simulation was accomplished up to 20- deg angle of attack using a pair of modified hollow cylinder, flow-shaping devices and a 1/16-scale inlet model in the AEDC 1-Ft Transonic Wind Tunnel. This is an increase of 8 deg in pitch over the present geometric pitch limit of 12 deg. Inlet ramp and lip pressure data were used to verify the technique supported by Mach numbers measured in front of the inlet, pressures measured at the engine-face station, and inlet dynamic total-pressure data. The Mach number covered by the study was from 0.6 to 1.1.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1973
- Accession Number
- AD0769307
Entities
People
- R. L. Palko
Organizations
- Arnold Engineering Development Complex