In the wind tunnel circular cylinder and airfoil models were provided in order to measure the relative head differences at the various air-flow velocity.The results of this study were as follows:⑴ The pressure coefficients of circular cylinder model were shown qualitatively similar distribution, not influenced greatly by air-flow velocity in the fluid-flow field. ⑵ When angle of attack α is 0°, the pressure coefficients of the airfoil model were not shown large difference at the air-flow velocity, but in general, they were increased as the air-flow velocity was increased. In addition, the pressure coefficients were shown qualitatively similar distribution in all velocities. ⑶ The airfoil model has had smaller change in pressure coefficient than the circular cylinder model. ⑷ The pressure coefficient of the airfoil model based on the angle of attack α has had remarkable difference in increase and decrease as X/C has been getting smaller.
Ⅰ. 서론
Ⅱ. 관련 이론
Ⅲ. 실험 장치 및 방법
Ⅳ. 실험 결과 및 고찰
Ⅴ. 결론