Flow control study of a NACA 0012 airfoil with a Gurney flap was carried out in a wind tunnel, where it was demonstrated that a dielectric-barrier-discharge (DBD) plasma actuator attached to the flap could increase the lift further, but with a small drag penalty. Time-resolved PIV measuremen...
The test model used was a NACA 0012 airfoil with the chord length c = 100 mm and the span b = 250 mm, giving the aspect ratio b/c = 2.5. Tests were carried out at three free-stream velocities of U? = 3.0, 4.3 and 5.3 m/s, corresponding to Reynolds numbers Re = 20,000, 28...
These effects are neglected in the 2D numerical model. To visualize the laminar separation bubble, vorticity contour maps were prepared around the airfoil (Figure 16). This drawing was made for four angles of attack: 0 deg, 4 deg, 8 deg and 11 degrees. In addition, this picture shows the...