现代超临界翼型设计及其风洞试验  

Design and wind tunnel test investigation of the modern supercritical airfoil

作　　者：孙智伟[1] 白俊强[1] 高正红[2] 肖春生[2] 郝礼书[2] 

机构地区：[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

出　　处：《航空学报》2015年第3期804-818,共15页Acta Aeronautica et Astronautica Sinica

基　　金：翼型叶栅空气动力学国家重点实验室基金(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。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.

关 键 词：翼型 优化 气动阻力 跨声速气动力 风洞试验 激波 

分 类 号：V211.411.2[航空宇航科学与技术—航空宇航推进理论与工程]