Abstract
An experimental investigation of hingeless flow control by vortex breakdown manipulation over a delta wing is described. Employed as a method of longitudinal control for slender-wing planforms, the performance of this active flow control technique was evaluated as a possible replacement to conventional moving or hinged control surfaces. Testing was conducted with a 60-deg delta-wing model incorporating pneumatic vortex control (PVC) actuators. These actuators delivered high-pressure jets of varying parameters on the upper surface of the model. The jets were used to alter the flowfield over the wing caused by leading-edge vortices. The natural location of vortex breakdown was shifted by three sets of PVC actuators strategically positioned on the model. This effect was intended to control the chordwise lift distribution over the wing by inducing both premature and delayed vortex breakdown, resulting in nose-up and nose-down pitch responses, respectively. A comparative analysis of this hingeless flow control concept was conducted in Texas A&M University's 3 × 4 ft low-speed wind tunnel and 2 x 3 ft water tunnel
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