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 1. Test Technique Evaluation
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 determine 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 wind tunnelflight correlation to define the validity of current wind tunnel test techniques to provide data for full-scale flight performance predictions. Surface pressure data were obtained on several model configurations, using a wingtip support system, to define the effects of nozzle closure and jet exhaust flow on the test article nacelle and nozzle surfaces. Two additional test entries were conducted on sting support systems to evaluate support system interference produced by the wingtip support system and to evaluate the annular- jet test technique.
- Attack and Fighter Aircraft
- Jet and Gas Turbine Engines