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    • 6. 发明申请
    • Apparatus and Method for Aerodynamic Drag Reduction
    • 用于气动阻力减小的装置和方法
    • WO2011098807A1
    • 2011-08-18
    • PCT/GB2011/050234
    • 2011-02-09
    • THE UNIVERSITY OF SHEFFIELDQIN, Ning
    • QIN, Ning
    • B64C23/04
    • B64C23/04
    • An apparatus and method for reducing aerodynamic drag is disclosed. The apparatus and method is adapted to reduce wave drag and profile (form) drag associated with aerodynamic bodies, wings, rotor blades, or other aerodynamic surfaces operating in the transonic regime. In one embodiment, a three dimensional bump (100, 500) is disclosed, adapted for location on the surface of an aerodynamic body, having a curved upper surface (120, 140, 160, 180, 200) which redistributes the pressure of a normal shockwave generated on the aerodynamic body and at least one integral vortex generator (300, 550) arranged to generate a stream-wise vortex downstream of the bump. The combined effect of the bump (100, 500) and the vortex generator (300, 550) is to reduce the wave drag associated with the shock wave and to avoid or delay the post-shock boundary layer separation, thereby reducing form drag.
    • 公开了一种用于减小气动阻力的装置和方法。 该装置和方法适于减少与空气动力学体,翼,转子叶片或在跨音速状态下操作的其它空气动力学表面相关联的波浪阻力和轮廓(形式)阻力。 在一个实施例中,公开了适于位于空气动力体的表面上的三维凸起(100,500),其具有弯曲的上表面(120,140,​​160,180,200),该上表面重新分布正常的压力 在空气动力体上产生的冲击波和至少一个积分涡流发生器(300,550),其布置成在凸块的下游产生流向涡流。 凸起(100,500)和涡流发生器(300,550)的组合效果是减小与冲击波相关联的波浪阻力,并避免或延迟冲击后边界层分离,从而减少形状阻力。