旋翼桨盘处的诱导速度分布采用自前向后直线增大的形式。
The distribution of induced velocity at the rotor is assumed linearly variable over the disk.
在机身影响下，旋翼近场尾涡形状发生畸变，从而改变桨盘处的诱导速度分布。
The results show that the rotor near-wake is distorted because of the flow field of the fuselage, resulting in large variation on the induced velocity distribution at the rotor plane.
在机身影响下，旋翼近场尾涡形状发生畸变，从而改变桨盘处的诱导速度分布。
The results show that the rotor near-wake is distorted because of the flow field of the fuselage, resulting in large variation on the induced velocity distribution at the rotor plane.
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