| 摘要 |
<p>PROBLEM TO BE SOLVED: To enlarge a maximum lift coefficient in a wide speed area ranging to a high speed area from a low speed area, and reduce a noise level by setting a wing type having the specific thickness ratio for substantially defining a front edge shape of the wing type by a front edge radius and the circle center as a reference. SOLUTION: Since the front edge upper surface contour, a front edge radius and a camber line are optimized more than a symmetrical wing having the thickness ratio 10% of NACA 0010, the pressure distribution in an upper surface of a wing type is flattened, a noise level of a main rotor rotating sound can be reduced by about several dB more than usual, a maximum lift coefficient Clmax is largely improved. An AK 100 G wing type can improve the maximum lift coefficient Clmax in a wide speed area more than an AK 100 D wing type. Thus, an actuation area of a helicopter blade can be expanded so that flight performance of a helicopter is improved. Since the maximum lift coefficient Clmax in a medium speed area is particularly improved, hovering performance is improved.</p> |
