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倾转过渡状态旋翼-机翼气动干扰特性计算分析

刘佳豪1,李高华2,王福新1   

  1. 1. 上海交通大学航空航天学院
    2. 上海交通大学船舶海洋与建筑工程学院; 上海交通大学航空航天学院
  • 收稿日期:2021-07-13 修回日期:2021-09-30 出版日期:2021-10-09 发布日期:2021-10-09
  • 通讯作者: 王福新
  • 基金资助:
    国家自然科学基金

Calculation Analysis of Rotor-Wing Aerodynamic Interference Characteristics in Transition Mode

  • Received:2021-07-13 Revised:2021-09-30 Online:2021-10-09 Published:2021-10-09

摘要: 本文针对倾转旋翼机倾转过渡状态旋翼-机翼之间的气动干扰开展了高分辨率数值模拟。计算采用有限体积法对积分形式的非定常Navier-Stokes方程进行离散,使用重叠网格处理旋翼桨叶与机翼之间的相对运动。背景网格采用基于八叉树结构的笛卡尔结构化网格,并使用基于无量纲Q准则的网格自适应技术来获得高分辨率尾迹流场。首先,计算了孤立旋翼和旋翼-机翼组合体悬停状态,根据计算结果证明高分辨率求解器对于旋翼气动力预测的准确性和旋翼尾迹结构演化的高分辨率特性,其中对比了旋翼-机翼组合体悬停状态IDDES和RANS计算结果,IDDES所得流场更为精细且气动力结果与RANS结果也有所差异。随后,对倾转过渡状态不同倾转角下旋翼-机翼组合体飞行状态进行了仿真计算,得到并分析了旋翼与机翼之间气动干扰流场。结果表明,在倾转过渡状态中期旋翼产生诱导滑流对机翼有着一定的升力增益效果,而倾转初期与末期则无明显升力增益,初期甚至为负增益;旋翼与机翼气动变化情况证明倾转过渡状态旋翼-机翼气动干扰对倾转旋翼气动性能有着重要影响。

关键词: 倾转旋翼机, 倾转过渡, IDDES, 漩涡流场, 气动干扰

Abstract: A high-resolution numerical simulation was carried out for the aerodynamic interference phenomenon between rotor and wing in tiltrotor conversion mode. The integral form unsteady N-S equations are discretized by the finite volume method, and the relative motion between rotor blade and wing is treated by overlapping grids. Back-ground grids adopts Cartesian structured grid based on octree structure, using grid self-adaptive technology based on non-dimensional Q criterion to obtain high-resolution wake. First, the hover states of isolated rotor and rotor-wing combination are calculated. According to the calculation results, the accuracy for rotor aerodynamic prediction and the high-resolution characteristics for rotor wake structure evolution of high-resolution solver are proved. The calcu-lation results of iddes and RANS in hovering state of rotor wing assembly are compared, The flow field obtained by IDDES is more fine, and the aerodynamic results are also different from the RANS results.Subsequently, the flight state of rotor-wing assembly under different tilt angles in conversion mode is carried out. Then the aerodynamic interference flow field between rotor and wing is obtained and analyzed. The results show that the induced slip-stream produced by the rotor in the middle of conversion state has a certain lift gain effect on the wing, but there is no obvious lift gain at the beginning and end of tilt-state, there is even negative gain at the beginning. The aero-dynamic variation of rotor and wing proves that rotor-wing aerodynamic interference in conversion mode has an important influence on the aerodynamic performance of tilt-rotor.

Key words: Tilt-rotor aircraft, Conversion mode, IDDES, Vortex flow field, Aerodynamic interference

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