The goal of the present study was to assess the roles of asymmetric leading-edge flap deflections on delta wings over a wide range of angle of attack, including attached and separated flow regimes. Experimental and computational modeling data were collected for both 80- and 65-deg delta wings with 20% conical flaps. A significant observation was that both wings exhibited a reversal in control effectiveness at an angle of attack dependent on sweep angle. The reversal behavior may result from the relative strengths of the longitudinal and crossflow effects.
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