Active Separation Control Measurements and Computations for a NACA 0036 Airfoil
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A 2D flow control wind tunnel model was designed based on the visualization of separation behavior as a function of angle of attack. The NACA 0036 airfoil model was pressure instrumented and equipped with synthetic jet flow control actuators at 30% and 65% chord on both sides of the model. Wind tunnel measurements of the airfoil pressure distribution and wake velocity surveys were conducted for a wide range of actuator performance and configuration at angles of attack from 0 to 10 degrees . The test results illustrated the importance of actuator slot position with respect to the separation location. The 65% slot location provided the most effective separation control for 0 and 5 degrees angle of attack, while the 30% slot location was most effective at 10 degrees . For the test cases at 5 degrees , CFD results were obtained using an incompressible RANS method. The numerical results did not capture the separation locations for the base- line cases with no control. The CFD also predicted the opposite trend for the optimum slot location when compared with the measurements.
AIAA-03-3516, Orlando, FL, June 2003.
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