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The objective of this research is to investigate the efficacy of Circulation Control (CC) at low Reynolds numbers (Re=150,000) with relatively low blowing rates on a modified NACA0015 wing. Two dual radius flap geometries are developed and tested by varying specific flap parameters from a previously studied baseline configuration. A two-dimensional (2-D) low-speed wind-tunnel experimental study is undertaken to evaluate the effect of trailing edge upper slot blowing at cruise flight, takeoff and landing (0 o , 30 o and 60 o flap deflection). The wind tunnel tests are conducted at Mach numbers of 0.03, with momentum coefficients of blowing (Cµ) ranging from 0.0 to 0.3. It is found that CC blowing is effective at all cases enabling the wing to achieve high lift-to-drag ratios and high lift augmentation during takeoff and landing. The modified NACA0015 with the smaller Coanda radius ratio (r2/r1) flap is found to be the most efficient at CC blowing achieving a maximum incremental lift coefficient (∆C l ) of 0.89 at 30 0 flap deflection. The lift-to-drag ratio is increased up to 11 times at δ f = 0 o flap deflection and α = 0 o using the same flap configuration.

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