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Two experimental studies were conducted to investigate the use of surface actuation devices to suppress stall on a NACA 0012 airfoil by preventing the bursting of the low Reynolds number leading edge separation bubble. Both a leading edge burst control plate and a leading edge dynamic roughness field were studied as actuation devices. Through the use of pressure measurements, force measurements, and particle image velocimetry (PIV) data, it is shown that these devices have the ability to suppress the leading edge separation bubble at higher angles of attack than an airfoil without such devices. With the increased stall angle obtained through the use of these devices, lift performance is increased.

Experimental study of low Reynolds number flow control devices: dynamic burst control plate and dynamic roughness