A Method to Increase the Full-Scale Inlet/Engine System Testing Capability of the AEDC 16-ft Transonic Wind Tunnel
Final rept. Jan 1971-Jul 1972
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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A study was conducted of a new testing technique using flow shaping that together with some modifications of the AEDC 16-ft Transonic Propulsion Wind Tunnel will provide the capability to test full-scale inletengine configurations with forebody effects at high maneuvering angles at transonic velocities. The method used to obtain the flow simulation for high maneuvering angles utilized auxiliary flow shaping and geometric pitch. An analytical potential flow method was used to determine the configuration of devices necessary to produce the required flow fields these devices were then checked experimentally to verify the results.
- Test Facilities, Equipment and Methods
- Jet and Gas Turbine Engines