抄録
The flow around a two-dimensional isolated airfoil is visualized in a smoke wind tunnel. The test airfoil consists of the leading and trailing parts, which is fixed on the test section wall. The leading one can be rotated not more than 9 degrees around the point of 1/4 chord length. The flow visualization was carried out under the following conditions; Reynolds Number Re=1.01×104-2.82×10 5, attack angle α=0-20 degrees. The visualized result shows that the shape changing can control the flow field around the airfoil near the stall angle of the original shape.
