航空学报 > 2015, Vol. 36 Issue (3): 804-818   doi: 10.7527/S1000-6893.2014.0188

现代超临界翼型设计及其风洞试验

孙智伟1, 白俊强1, 高正红2, 肖春生2, 郝礼书2   

  1. 1. 西北工业大学 航空学院, 西安 710072;
    2. 西北工业大学 翼型叶栅空气动力学国家重点实验室, 西安 710072
  • 收稿日期:2014-05-26 修回日期:2014-08-14 出版日期:2015-03-15 发布日期:2015-03-31
  • 通讯作者: 白俊强 男,博士,教授,博士生导师。主要研究方向:飞行器总体气动布局设计、部件气动力设计、多学科优化设计、计算流体力学理论和应用。Tel: 029-88492694 E-mail: junqiang@nwpu.edu.cn E-mail:junqaing@nwpu.edu.cn
  • 作者简介:孙智伟 男,博士研究生。主要研究方向:飞行器气动伺服弹性、气动伺服弹性主动控制、多学科优化设计、飞行器气动力设计。Tel: 13636810240 E-mail: zhiwei@mail.nwpu.edu.cn
  • 基金资助:

    翼型叶栅空气动力学国家重点实验室基金 (9140C4203011005)

Design and wind tunnel test investigation of the modern supercritical airfoil

SUN Zhiwei1, BAI Junqiang1, GAO Zhenghong2, XIAO Chunsheng2, HAO Lishu2   

  1. 1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
    2. National Key Laboratory of Science and Technology on Aerodynamic Design and Research, Northwestern Polytechnical University, Xi'an 710072, China
  • Received:2014-05-26 Revised:2014-08-14 Online:2015-03-15 Published:2015-03-31
  • Supported by:

    National Key Laboratory of Science and Technology on Aerodynamic Design and Research Foundation (9140C4203011005)

摘要:

开展了现代超临界翼型的设计研究,对现役飞机的压力分布形态进行了分析,针对现役飞机在巡航状态和阻力发散点的压力分布进行对比,提取了现役飞机超临界剖面设计的要点。采用类函数/型函数变换(CST)参数化方法、基于二阶震荡及自然选择的随机权重混合粒子群算法(RwSecSelPSO)、雷诺平均Navier-Stokes(RANS)方程、Kriging代理模型结合定期望值型的目标函数建立了优化设计系统。针对提高阻力发散马赫数和降低巡航低头力矩的设计指标,利用优化设计系统通过调整目标期望值设计了一系列满足设计指标但阻力发散马赫数不同的超临界翼型,并选择了其中具有典型特性的翼型进行了对比分析,验证了提高阻力发散马赫数和低速失速特性的设计方法,指出了在阻力发散点形成平顶形压力分布的超临界翼型具有较好的综合性能。对设计的超临界翼型进行了高、低速风洞试验验证,试验结果表明:设计结果达到了设计指标要求,提出的低速改进方案有效,层流对超临界翼型失速特性影响较大。

关键词: 翼型, 优化, 气动阻力, 跨声速气动力, 风洞试验, 激波

Abstract:

In this paper, the aerodynamic design of modern supercritical airfoil is researched, the pressure distributions of outboard wing of two aircraft in service are analyzed at cruise and drag divergence point respectively, and some key points of supercritical section aerodynamic design are extracted. The class function/shape function transformation (CST) parametric method, Random weighted hybrid partical swarm optimization algorithm based on second order oscillation and natural selection (RwSecSelPSO), Reynolds averaged Navier-Stokes (RANS) equations and Kriging surrogate model combined with a kind of given expectation value cost function are used to establish the optimization system. In order to increase drag divergence Mach number and reduce the nose down moment, a series of airfoils satisfying the requirement but with different drag divergence Mach numbers is designed by the optimization system by adjusting the expectation value, meanwhile some airfoils with typical pressure distribution are compared and analyzed; the design principles and methods of improving drag divergence point and low-speed stall characteristic are verified and the airfoil which has flat topped pressure distribution at drag divergence point has better performance. Wind-tunnel tests are conducted for stall improvement method and transonic aerodynamic characteristic; the wind-tunnel test results indicate that the aerodynamic design satisfies the requirement and the stall improvement method is effective, while the laminar flow affects the stall characteristic dramatically.

Key words: airfoils, optimization, aerodynamic drag, transonic aerodynamics, wind tunnel test, shock waves

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