大展弦比运输机标模高升力构型设计与评估  

Design and Evaluation of High Lift System Configuration for High-aspect Ratio Aircraft Calibration Model

作　　者：李聪[1] 魏闯[1] 徐建东[1] 黄文吉[1] 张铁军[1] 

机构地区：[1]中国航空工业空气动力研究院,黑龙江哈尔滨150001

出　　处：《航空计算技术》2012年第5期91-94,共4页Aeronautical Computing Technique

摘　　要：介绍了中国航空工业空气动力研究院基于分层策略遗传算法的多段翼型优化设计工具和高升力构型计算评估方法,参照国内外大展弦比运输机指标为FL-9增压风洞设计了高升力构型标模,为检验标模气动性能,在法国ONERA F1风洞进行了一系列风洞试验和采用UNSMB平台进行了数值模拟。结果显示计算结果与试验结果有着较好的一致性,设计方案具有较好的增升效果。An introduction is given of optimization system of multi-element airfoil basic on hierarchic genetic algorithm and evaluation method of high lift system configuration aerodynamic performance.According to design index of high-aspect ratio transporters at home and abroad,a high lift system configuration calibration model for AVIC ARI FL-9 wind tunnel has been designed.To determine the aerodynamic characteristics of the model,several wind tunnel tests were conducted in ONERA F1 Wind Tunnel and Navier-Stokes calculations were performed using CFD software UNSMB.The calculated results are in general agreement with the experimental data,and the design result of high-lift devices has good lift-enhancing.

关 键 词：遗传算法 大展弦比 高升力构型 数值计算 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]