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1272 PATEL ET AL. 0.9 0.8 0.7 0.6 0.5 0.4 0.3 0.2 0.1 0 0.85 0.80 0.75 CL 0.70 0.65 0.60 0.35 0.30 0.25 0.20 0.15 0.10 0.05 0.00 c) CL a) 0 5 Angle of Attack, deg 25 CL a) CL b) 0.35 0.30 0.25 0.20 CD c) 10 15 20 A A A A c c c c t t t t u u u u a a a a t t t t o o o o r r r r - - - - O O O O fF F Ff -F F FB- - - 4B B B 4 4 4 A A A A c c c c t t t t u u u u a a a a t t t t o o o o r r r r - - - - O O O O nN N N - - - - P P P P 1 1 1 1 8 8 8 8 Effects of plasma actuators on the lift coefficient (top) and drag Fig. 12 polar (bottom) of the 47-deg swept wing for a range of angles of attack; P18: a pair of unsteady plasma actuators on the inboard section (one on the wind side and the other on the lee side); B4: baseline. IV. Conclusions An experimental investigation was conducted to investigate the use of DBD plasma actuators for longitudinal control of a 1303 UCAV planform at high angles of attack with no moving surfaces. Control was implemented at the wing leading edge to provide longitudinal control without the use of hinged control surfaces. The concept employed the use of lee-side and wind-side plasma actuators at the wing leading edge to alter the aerodynamic lift and drag distributions over the 1303 planform by manipulating the flowfield over the lee side of the wing section. Data acquisition included force- balance measurements, laser fluorescence, and surface flow visualizations. Flow visualization tests mainly focused on understanding the vortex breakdown phenomena over the baseline uncontrolled wing Effects of plasma actuators on the lift coefficient (top) and drag A ctuator-OfFf-FB-4B4 A ctuator-OnN-P19 Angle of Attack, deg 0.85 0.80 0.75 0.70 0.65 0.60 15 17 19 21 23 25 A ctuator-OfFf-FB-4B4 A A A A A A A A c c c c c c c c t t t t t t t t u u u u u u u u a a a a a a a a t t t t t t t t o o o o o o o o r r r r r r r r - - - - - - - - O O O O O O O O nN N N N N N N - - - - - - - - P P P P P P P P 1 1 1 1 1 1 1 1 9 9 9 9 9 9 9 9 b) CD Angle of Attack, deg 15 17 Angle of Attack, deg 25 A ctuator-OfFf-FB-4B4 A ctuator-OnN-P18 19 21 23 0 0.2 0.4 0.6 CL 0.8 1 0.15 0.10 0.05 0.00 A ctuator-OfFf-FB-4B4 A A A A c c c c t t t t u u u u a a a a t t t t o o o o r r r r - - - - O O O O nN N N - - - - P P P P 1 1 1 1 8 8 8 8 0 0.2 0.4 0.6 CL 0.8 1 A ctuator-OfFf-FB-4B4 A ctuator-OnN-P19 Fig. 13 polar (bottom) of the 47-deg swept wing for a range of angles of attack; P18: a pair of unsteady plasma actuators on the inboard section (one on the wind side and the other on the lee side); B4: baseline. C L 1.000 0.800 0.600 0.400 0.200 0.000 0 10 20 30 40 P15,P18,,PP1199 P9,P10 Plalas msamOaf f Off PlalasmsamOan On Angle of Attack, deg Effects of unsteady plasma actuators on the lift coefficient at Fig. 14 high angles of attack. 0.9 0.8 0.7 0.6 0.5 0.4 0.3 0.2 0.1 0 0 5 10 15 20 25PDF Image | Plasma Actuators for Hingeless Aerodynamic Control of an Unmanned Air Vehicle
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