摘要
采用光固化快速成型技术（SL）加工基于气动/结构耦合分析的六套不同机翼优化构型的轻质F4模型,在0.6m跨超声速风洞完成了马赫数0.6-0.85范围内的气动力测量试验。试验结果表明,采用气动/结构耦合优化设计的代号为6#的轻质F4模型升力特性与国外结果较接近,与机翼三维变形的事实吻合,验证了采用的气动/结构耦合优化设计方法基本可行,为探索模型静气动弹性风洞试验数据修正方法提供了参考。
Six F4 test models with different wing configurations optimization were manufactured by Stereo-Lithography（SL） technique.Their structural design optimization was accomplished by coupling aerodynamic and structural method.An experiment was conducted to obtain their aerodynamic force characteristics at Mach numbers of 0.6 to 0.85 in a 0.6m transonic and supersonic wind-tunnel.The experimental results indicate that the lift force characteristic of F4 model named 6# is accord with other results in references,which shows good agreement with three-dimension deformations for wings.Therefore,the coupling aerodynamic and structural design optimization method is feasible,which provides some support to study static aero-elastic modification method for wind-tunnel test data.
出处
《实验流体力学》
EI
CAS
CSCD
北大核心
2010年第6期38-40,60,共4页
Journal of Experiments in Fluid Mechanics
基金
国家“973”计划课题(2009CB723802)
国家自然科学基金(51075385)
关键词
轻质F4模型
优化构型
气动特性
光固化快速成型
light-weight F4 models
configurations optimization
aerodynamic forces
stereo-lithography
