Abstract
A low-speed wind-tunnel test was conducted to determine the lateral-directional control effectiveness of a forebody jet nozzle blowing on a 10% scale F-15E model. This investigation of pneumatic forebody vortex flow control was the first of its kind performed on an F-15 configuration. The test acquired sixcomponent force balance data in the NASA Langley 30- by 60-Foot Tunnel at a freestream dynamic pressure of 8 psf at an equivalent Reynolds number per foot of approximately 5.08 X 10 5. Asymmetric forebody jet blowing was effective in generating yawing moments through an angle of attack (AOA) range that extends beyond the limit of rudder control power. The optimum nozzle configurations were pointed outward, and yawing moments generated within the maneuver range of AOA (a < 40 deg) increased with increases in both blowing rate and AOA. Above 10-deg AOA, blowing rates of C M = 0.010 and greater resulted in yawing moments that approached or exceeded that developed by full rudder deflection.
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