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1270 PATEL ET AL. secondary separation vortex breakdown vortex breakdown α = 5 deg Fig. 8 Wind-tunnel flow visualization photographs of the lee side of a 47-deg swept wing with a blunt leading edge. plasma configurations on the lift coefficient and drag polar, respectively, for angles of attack ranging from 0 to 35 deg. A comparison of the effects of P9, P10, and P15 with the baseline (B1/ B4) reveals noticeable effects of the plasma actuators for > 15 deg, at which the VBD occupies most of the leading edge. There is negligible difference between the effects of P9 and P10 for all angles of attack tested (see Figs. 11a–11d), which suggests that the effects of plasma control on the leeward surface are similar for the inboard and outboard sections of the wing. However, Figs. 11c and 11f demonstrate a significant rise in the lift coefficient and a shift in the drag bucket, respectively. Plasma configuration P15 uses two unsteady actuators at the leading edge, slightly on the windward side. Studies have shown that at higher angles of attack, the primary separation location moves upstream, closer to the windward side of the wing, which seems to explain why P15 is more effective than P9 and P10. Additional tests were conducted to verify this speculation and results from the new actuator configurations P18 and P19, which also used actuators slightly on the wind side. Results shown in Figs. 12 and 13 confirmed the effects of the leading-edge flow control observed earlier. Figure 14 summarizes the effects of the most promising plasma actuator configurations with the baseline case (no control) for ranging from 0- to 35-deg angles of attack. At conditions in which the flow was nominally separated from the wing leading edge, the plasma actuators were able to produce significant control forces compared with those of the conventional trailing-edge flap/aileron. Effective control through the use of plasma actuators was observed through 15 to 35 deg. Figure 15 shows a comparison of the plasma actuator effects with the conventional flap/ aileron cases and the control-off case. This demonstrates the significant control forces that were generated using plasma actuators at high angles of attack. α = 10 deg α = 15 deg Fig. 9 Wind-tunnel flow visualization photographs of the lee side of a 47-deg swept wing with a blunt leading edge.PDF Image | Plasma Actuators for Hingeless Aerodynamic Control of an Unmanned Air Vehicle
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