A single ejector equipped with only one vector control jet and a diffuser flap was installed close to the leading edge of the strake of a one-fifth scale, semi-span model of the aircraft, without wing, canard, or tail surface. Tests of the system at a nozzle pressure ratio of 1.24 indicated a thrust augmentation of 1.92 and a thrust in the flight direction of about 12% of the total thrust under static conditions. An ejector stall occured at a ratio of tunnel dynamic pressure to nozzle gage pressure of about 0.008. Ejector stall speed can be delayed by using a boundary layer control jet at the front inlet lip of the ejector.
A Jet-Diffuser Ejector for for a V/STOL Fighter
1981
50 pages
Report
No indication
English
Jet & Gas Turbine Engines , Aircraft , Aerodynamic stalling , Ejectors , Exhaust diffusers , General dynamics aircraft , Scale models , V/stol aircraft , Wind tunnel tests , Aircraft performance , Attack aircraft , Boundary layer control , Conical nozzles , Strakes , Thrust vector control , NTISNASA
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