航空学报 > 2015, Vol. 36 Issue (10): 3275-3283   doi: 10.7527/S1000-6893.2014.0345

超临界翼型低雷诺数流动分析及优化设计

王科雷, 周洲, 许晓平, 甘文彪   

  1. 西北工业大学 航空学院, 西安 710072
  • 收稿日期:2014-10-10 修回日期:2014-12-11 出版日期:2015-10-15 发布日期:2014-12-17
  • 通讯作者: 周洲, Tel.: 029-88453368 E-mail: zhouzhou@nwpu.edu.cn E-mail:zhouzhou@nwpu.edu.cn
  • 作者简介:王科雷 男, 博士研究生。主要研究方向: 飞行器总体设计, 气动布局设计。 E-mail: ak203201@163.com;周洲 女, 教授, 博士生导师。主要研究方向: 飞行器总体设计, 气动布局设计。 Tel: 029-88453368 E-mail: zhouzhou@nwpu.edu.cn
  • 基金资助:

    总装预研基金 (513250101)

Flow characteristics analysis and optimization design of supercritical airfoil at low Reynolds number

WANG Kelei, ZHOU Zhou, XU Xiaoping, GAN Wenbiao   

  1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China
  • Received:2014-10-10 Revised:2014-12-11 Online:2015-10-15 Published:2014-12-17
  • Supported by:

    PLA General Armament Department Pre-Research Foundation of China (513250101)

摘要:

以高空长航时无人机(UAV)翼型研究为背景,对超临界RAE2822翼型在高空高亚声速下的低雷诺数气动特性进行了数值模拟及优化设计研究。采用求解雷诺平均N-S方程的有限体积法,对典型低雷诺数下RAE2822翼型绕流进行数值模拟,验证了SST k-ω湍流模型的可靠性和准确性;基于不同高度不同雷诺数下RAE2822翼型的计算气动力对比分析,研究了高度增大所带来的低雷诺数效应;通过对低雷诺数下超临界翼型表面流场结构及流动机理的详细分析,提出了一种弱化激波的翼型设计思想,并通过优化算例验证了该思想的可行性。

关键词: 高空长航时无人机, 超临界翼型, 低雷诺数, 流场结构, 流动机理, 优化设计

Abstract:

Based on the research of the high-attitude long-endurance solar unmanned aerial vehicle (UAV), the aerodynamic performances and optimization design of the supercritical airfoil RAE2822 at high subsonic speed and low Reynolds number are numerically simulated and studied. To verify the accuracy and reliability of the SST k-ω turbulence model, finite volume method is used to solve the 2D Reynolds-averaged Navier-Stokes equations for the numerical simulations of the fluid around RAE2822 at typical Reynolds number. Meanwhile, a detailed analysis of the aerodynamic forces among different altitudes is conducted and the low Reynolds effects are summarized, then the high subsonic and low Reynolds number flow characteristics are researched by analyzing the fluid structure and flow mechanism around RAE2822. Finally, an optimization concept of weakening the shock waves is proposed for the supercritical airfoil design at high subsonic speed and low Reynolds number, whose feasibility is tested and verified by an optimization case.

Key words: high-attitude long-endurance unmanned aerial vehicle, supercritical airfoil, low Reynolds number, fluid structure, flow mechanism, optimization design

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