Performance of Steady and Intermittent Blowing Jet Flaps and Spanwise Upper Surface Slots.
Final rept. Apr 73-Nov 75,
MCDONNELL AIRCRAFT CO ST LOUIS MO
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A wind tunnel test was conducted in the NASA Ames 14 foot wind tunnel to determine the performance of steady and pulsed blown jet flaps and constant percent chord spanwise upper surface slots and to provide wing load and tail power data for a proposed Air Force COMMA Composite Maneuver Augmentation RPV flight test program. The tests were performed on a 72.1 scale semi-span model of the proposed vehicle with a wing leading edge sweep of 45 deg over a Mach number range of 0.4 to 1.1. The Reynolds number was approximately 4 million per foot and the angle of attack range was -5 deg to 25 deg. Full and partial span jet flaps jet flap angles of 30 deg, 60 deg and 80 deg 40 and 70 constant chord slots and horizontal tail deflections of 2 deg, 0 deg, -2 deg, -4 deg and -6 deg were tested over a blowing momentum coefficient range of 0 to 0.018. Balance forces, wing upper and lower surface static pressures, wing root bending moment, wing tip accelerometer, and flow visualization data were obtained. The results in general indicated that slot blowing was ineffective, jet flaps provided lift augmentation at all angles of attack tested and drag reduction at high lift conditions, and pulsed blowing provided minor benefits over steady blowing. Trimmed jet flap data indicates a Mach dependence on jet flap performance and that jet flaps provide a performance advantage onl at high lifts. Author
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- Pilotless Aircraft