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1. 发明授权

US06315522B1 Helicopter blade aerofoil and helicopter blade 有权
标题翻译：直升机叶片翼型和直升机叶片
公开(公告)号：US06315522B1
公开(公告)日：2001-11-13
申请号：US09511802
申请日：2000-02-23
申请人： Eiichi Yamakawa , Akihiko Tsuchihashi , Kenjiro Inagaki
发明人： Eiichi Yamakawa , Akihiko Tsuchihashi , Kenjiro Inagaki
IPC分类号： B63H126
CPC分类号： B64C27/467 , Y10S416/05
摘要： Upper and lower faces of a helicopter blade aerofoil are defined by the following coordinates. TABLE 1 X/C Yup/C Ylow/C 0.00000 0.00000 0.00000 0.00100 0.00511 −0.00584 0.00250 0.00843 −0.00813 0.00500 0.01218 −0.01014 0.00750 0.01505 −0.01136 0.01000 0.01747 −0.01218 0.01250 0.01959 −0.01277 0.01500 0.02150 −0.01328 0.01750 0.02325 −0.01375 0.02000 0.02487 −0.01415 0.02500 0.02780 −0.01483 0.05000 0.03891 −0.01714 0.07500 0.04682 −0.01862 0.10000 0.05291 −0.01979 0.15000 0.06152 −0.02206 0.20000 0.06666 −0.02470 0.25000 0.06892 −0.02729 0.30000 0.06895 −0.02949 0.35000 0.06841 −0.03109 0.40000 0.06744 −0.03211 0.45000 0.06568 −0.03270 0.50000 0.06301 −0.03272 0.55000 0.05943 −0.03211 0.60000 0.05498 −0.03084 0.65000 0.04968 −0.02883 0.70000 0.04349 −0.02600 0.75000 0.03649 −0.02237 0.80000 0.02886 −0.01794 0.85000 0.02087 −0.01315 0.90000 0.01279 −0.00777 0.95000 0.00538 −0.00304 1.00000 0.00236 −0.00095 leading edge radius r/C=0.0096 center of circle X/C=0.0097, Y/C=−0.0018 Accordingly, the maximum lift coefficient Clmax is large in a wide velocity range from lower velocity to higher velocity, and reduction of noise level and pitching moment can be achieved.
摘要翻译：直升机叶片机翼的上下面由以下坐标定义：前缘半径r / C = 0.0096圆心X / C = 0.0097，Y / C = -0.0018因此，最大升力系数Clmax大可以实现从较低速度到较高速度的宽速度范围，以及噪声水平和俯仰力矩的降低。

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