Wind Tunnel Results from a Nozzle Afterbody Test of a 0.2-Scale Fighter Aircraft in the Mach Number Regime of 0.6 to 1.5. Volume II. Model Configuration and Environment Effects.
Final rept. Jul 1977-Sep 1978
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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An investigation was conducted in the Propulsion Wind Tunnel 16T to document the effect of throttle-dependent parameters nozzle closure and nozzle pressure ratio on the aft end surface pressures of a 0.2-scale model of a twin- engine fighter prototype YF-17. The data are part of a data base to be used in a future analysis effort to define the validity of current wind tunnel test techniques to provide data for full-scale flight performance predictions.
- Attack and Fighter Aircraft
- Jet and Gas Turbine Engines