旋翼翼型气动设计与验证方法

Aerodynamic design and verification methods of rotor airfoils

为满足我国直升机研发对自主旋翼翼型的迫切需求,开展了旋翼翼型气动优化设计与验证方法研究。发展了旋翼翼型指标分析与给定方法,给出了我国直升机旋翼翼型谱系规划设想,以进化多目标算法为基础结合PCA算法建立了旋翼翼型多点/多目标优化设计方法,突破了旋翼翼型气动特性精准测量风洞试验技术。利用所建立的方法对典型厚度翼型进行了优化设计并开展了风洞试验验证,计算评估与试验验证均表明自主设计翼型综合性能较国外参考翼型有一定提升。在此基础上,进一步构建了旋翼性能理论计算与试验验证综合评估方法,两种方式得到的旋翼主要性能数据偏差小于5%,表明该方法具有较高的可靠性。评估结果显示,基于设计翼型的旋翼模型气动性能较基于参考翼型的旋翼模型提升了3%。

In order to meet the urgent needs of next-generation helicopters for independent-designed high-performance rotor airfoils,a study on the aerodynamic optimization design and verification method of rotor airfoils has been carried out.The analyze and setting methods of rotor airfoil performance indicators are developed,and the helicopter rotor airfoil pedigree planning is proposed as well.Based on the evolutionary multi-objective algorithm combined with the principal component analysis(PCA)algorithm,a multi-point/multi-objective optimization design method for rotor airfoils is established.The method is then used to optimize the design of airfoils with typical thicknesses.Aerodynamic performance of the optimized airfoils are verified by wind-tunnel experiments in which breakthrough in the accurate measurement of rotor airfoil aerodynamic characteristics has been achieved.Both computational and experimental results show that the comprehensive performance of the designed airfoil has an improvement to some extent compared with the reference one.On this basis,a comprehensive evaluation method for theoretical calculation and experimental verification of rotor performance is constructed.The deviation of the main performance indicators of the rotor obtained by the two methods is less than 5%,indicating that the method is highly reliable.The evaluation results show that the aerodynamic performance of the rotor model based on the designed airfoil is improved by 3%compared with the one based on the reference airfoil.