Turbine Engine Multi-Mission Propulsion Simulator Wind Tunnel Demonstration.
Abstract
A turbine engine multi-mission propulsion simulator, developed by the Air Force Aero Propulsion Laboratory (AFAPL) to permit improved aircraft performance prediction capability through the simultaneous simulation of inlet/airframe/nozzle flowfields, was successfully demonstrated in a wind tunnel model tested in the Arnold Engineering Development Center 16 ft. Transonic Tunnel. The model tested is simple, featuring the forebody, inlet and nozzle of an advanced fighter aircraft, but no wings or tail surfaces. It is adaptable to three different test modes - simulator - equipped, conventional aero flow-through and conventional jet effects, and provides for the simultaneous measurement of the total airframe, aft-end and simulator forces and moments. Extensive pressure instrumentation is also provided on the fuselage for flowfield interaction studies. Wind tunnel test data was obtained from Mach 0.6 to 1.45, and at angles of attack from -1.6 to 16 degrees. The results of the test indicate that the propulsion simulator is a viable wind tunnel test tool that can be effectively operated under realistic test conditions. Comparison of the aerodynamic performance of this configuration, as obtained from both simulator and conventional test techniques, showed relatively small differences, thereby indicating small inlet/aft-end flowfield interactions for this inlet/nozzle spacing. Data repeatability obtained with the simulator model was comparable to that obtained on the conventional models. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1976
- Accession Number
- ADA034282
Entities
People
- M. F. Eigenmann
- R. L. Bear
- T. C. Chandler
Organizations
- McDonnell Aircraft Corporation