倾转旋翼-机翼气动干扰准定常多重参考系仿真和风洞试验
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V211.41

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中央高校基本科研业务经费(XJJ2018028)


Qusi-steady Multiple Reference Frame Simulation and Wind tunnel Test for the Aerodynamic Interference between Tilt-rotors and Wings
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    摘要:

    倾转过渡状态下气动力的急剧变化是导致倾转旋翼飞行器姿不稳定重要原因。采用风洞试验和数值仿真方法研究前飞状态和倾转过渡状态倾转旋翼对机翼的气动干扰。首先,分别计算了悬停状态标模和前飞状态8038旋翼的拉力,数值仿真结果与试验结果符合良好。然后,针对倾转旋翼-机翼气动干扰建立了计算流体力学(computational fluid dynamics,CFD)数值仿真模型和搭建了风洞试验平台。结果表明:前飞状态随着前进比的增大机翼气动力系数降低且趋于与单机翼气动特性一致。倾转过渡状态,当旋翼倾角小于75°,随着前进比的增大机翼升力系数由负值逐渐增大。倾转角对机翼气动特性的影响随前进比的增大而降低。分析了倾转旋翼-机翼在升力方向和前飞方向上的气动力,研究结果对进一步完善倾转旋翼飞机设计及试飞试验成功提供了参考。

    Abstract:

    The dramatic change of aerodynamic performance in the tilt transition state is an important reason for the attitude instability of tilt-rotor aircraft. The aerodynamic interactional of the tilt-rotor on the wing in hover and transition modes was studied by wind-tunnel tests and numerical simulation. The numerical method was firstly applied in a benchmark rotor in hover and model 8038 in level flight, respectively. The simulated thrust agrees with the results from experiment. Then the computational fluid dynamics(CFD) model and wind-tunnel platform were established for the model of tilt-rotor/wing aero-interaction. The results show that the aerodynamic coefficients of wing decrease with the increase of advance ratio, and the aerodynamic performances of wing are consistent with the clean wing as the advance ratio large enough. With the tilt angle less than 75°, the lift coefficient increases from a negative value with the increase of advance ratio in transition state. The influence of tilt angle on the aerodynamic performances of the wing decreases with the increase of advance ratio. The aerodynamic forces of tilt-rotor/wing in the direction of lift and forward flight were analyzed, the research results provide a reference for further improving the design of tilt rotor aircraft and the success of flight test.

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杨海涛,夏 巍,帅 超,等. 倾转旋翼-机翼气动干扰准定常多重参考系仿真和风洞试验[J]. 科学技术与工程, 2021, 21(32): 13958-13964.
yanghaitao. Qusi-steady Multiple Reference Frame Simulation and Wind tunnel Test for the Aerodynamic Interference between Tilt-rotors and Wings[J]. Science Technology and Engineering,2021,21(32):13958-13964.

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历史
  • 收稿日期:2021-03-22
  • 最后修改日期:2021-09-16
  • 录用日期:2021-08-17
  • 在线发布日期: 2021-11-16
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