A wind tunnel model of a supersonic V/STOL fighter configuration has been tested to measure the aerodynamic interaction effects which can result from geometrically close-coupled propulsion system/airframe components. The approach was to configure the model to represent two different test techniques. One was a conventional test technique composed of two test modes. In the Flow-Through mode, absolute configuration aerodynamics are measured, including inlet/airframe interactions. In the Jet-Effects mode, incremental nozzle/airframe interactions are measured. The other test technique is a propulsion simulator approach, where a sub-scale, externally powered engine is mounted in the model. This allows proper measurement of inlet/airframe and nozzle/airframe interactions simultaneously. This is Volume 1 of 2: Wind Tunnel Test Pressure Data Report.
Propulsion and Airframe Aerodynamic Interactions of Supersonic V/STOL Configurations. Volume 1. Wind Tunnel Test Pressure Data Report
1985
885 pages
Report
Keine Angabe
Englisch
Propulsion Simulation Test Technique for V/STOL Configurations
SAE Technical Papers | 1983
|