民机标模高升力构型CAE-AVM-HL设计及验证  

Design and verification of high-lift configuration of civil aircraft standard model CAE-AVM-HL

作　　者：钟敏 华俊 王浩 白俊强[2] ZHONG Min;HUA Jun;WANG Hao;BAI Junqiang(Chinese Aeronautical Establishment,Beijing 100012,China;Northwestern Polytechnical University,Xian 710072,China)

机构地区：[1]中国航空研究院,北京100012 [2]西北工业大学,西安710072

出　　处：《空气动力学学报》2022年第4期158-167,共10页Acta Aerodynamica Sinica

摘　　要：气动标模高升力构型可用于起降状态复杂流动机理研究、CFD软件验证、低速风洞试验能力建设及增升系统噪声测试。民机气动标模高升力构型CAE-AVM-HL设计过程中采用基于代理模型的数值优化方法,优化流程包含样本建立、参数化几何外形、代理模型建立、遗传算法寻优。机翼增升装置形式为“前缘连续变弯下垂+前缘缝翼+后缘单缝富勒襟翼”。该民机气动标模高升力构型风洞测试模型在德国Deharde公司完成加工,在德荷大型低速风洞DNW-LLF完成风洞测试,试验马赫数0.2,雷诺数3×10^(6),测试内容包括测力、测压、测机翼和襟翼变形、转捩效应,以及丝线、油流、PIV试验等。针对前缘变弯下垂和前缘缝翼交界处的流动干扰现象,提出了抗流动分离的设计方案,CFD计算结果和风洞油流试验结果均显示设计方案缓解了前缘变弯下垂和前缘缝翼间的流动干扰。该构型最终风洞测量所得最大升力系数2.56,失速迎角19°,满足设计要求。The high-lift configuration of aerodynamic standard model can be used in various aspects,such as complex flow mechanism study,CFD software verification,low-speed wind tunnel capability research and aero-acoustic test.In the design process of the high-lift configuration of the civil aircraft aerodynamic standard model CAE-AVM-HL,numerical optimization based on the surrogate model is adopted.The optimization process includes sample establishment,geometry parameterization,surrogate model establishment and genetic algorithm optimization.The final form of the high-lift wing is featured with a variable camber droop-nose leading edge,a leading-edge slat and a single slot trailing-edge flap.The wind tunnel test model of civil aircraft aerodynamic standard model with high lift configuration CAE-AVM-HL was processed by Deharde company in Germany,and was tested in the German-Dutch large low-speed wind tunnel DNW-LLF at Mach number 0.2 and Reynolds number 3 million.The wind tunnel test includes force/pressure/deformation measurement,transition trip effect,silk tuft/oil flow,PIV measurement,etc.In view of the influence of the flow interaction between the droop-nose leading edge and the leading-edge slat,an anti-flow separation design scheme is proposed.Both CFD calculation and wind tunnel test show that the anti-flow separation design scheme alleviates the flow interference.The final measured maximum lift coefficient of the configuration is 2.56 and the stall angle of attack is 19°,which meet the design requirements.

关 键 词：气动标模 高升力 前缘变弯下垂 优化设计 风洞测试 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]