有翼ヘリコプタのホバリング性能に対する主翼位置の影響

抄録

A winged helicopter is one of the concepts to speed up a conventional helicopter. The wing contributes to the realization of high speed forward flight by sharing lift with the rotor. However, download is generated on the wing in low speed forward flight or hover because the wing is considerably exposed to the rotor downwash. This adverse force causes the deterioration of aircraft performance. Therefore, it is important to grasp aerodynamic performance in hover quantitatively and to conduct fundamental research to reduce the deterioration of aircraft performance. In this paper, experimental studies are conducted in order to measure rotor thrust and wing download in both OGE（Out of Ground Effect）and IGE（In Ground Effect）under the condition that the rotor torque coefficient is constant while changing the vertical and horizontal distance between the rotor and wing. From the experimental results, the influence of wing position with respect to the rotor on hovering performance such as the rotor thrust coefficient, the wing download coefficient, the ratio of the wing download coefficient to the rotor thrust coefficient and the effective thrust coefficient defined as the difference between the rotor thrust coefficient and the wing download coefficient are clarified.