Abstract
Separation control experiments were performed on airfoil models with freestream Mach numbers ranging from 0.1 to 0.5. This range of Mach numbers reaches into the transonic flow regime for the models tested. Pulsed jet control actuators were located near the airfoil leading edge. Experiments were performed to determine the effectiveness of the control actuators in reducing flow separation and augmenting lift. At low Mach numbers, the pulsed jet actuators produced up to a 50 percent increase in lift with only a small change in drag. The effectiveness of the actuators in improving airfoil performance degraded with increases in Mach number; however, even at the highest Mach number, modest lift enhancements were observed. In general, maximum performance benefits were observed for angles of attack equal to and above those corresponding to Cl(max) where severe flow separation exists in the uncontrolled flow. (Author)
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