摘要
为满足新一代高机动飞机气动性能评估、控制系统精确设计与高机动作战指标实现的需求,模型高速风洞大迎角俯仰动态特性探索及其试验数据精度的确定势在必行,且具有十分重要的工程意义。选取70°三角翼模型、SDM和Su-27飞机模型,在FL-24风洞的大振幅俯仰动态试验技术平台上对动态气动特性与试验数据精度进行了研究,获取了70°三角翼模型、SDM和Su-27飞机模型动态气动特性与重复性试验结果。研究结果表明:试验条件下,3种模型的动态数据精度较高,基本达到了高速风洞大迎角常规测力试验数据的精度水平。
It is important to determine pitching dynamic aerodynamic performance and test data precision of models with high angle of attack in high speed wind tunnel to meet the needs of evaluating aerodynamic performance,designing control system with precision and achieving maneuverability fight of aircraft.The dynamic performance and repeated test data precision of70°delta wing model,SDM and Su-27 fighter model with high angle of attack in the dynamic experimental system with large amplitude of FL-24 wind tunnel have been obtained,which can be used as a standard for investigations on dynamic test of models.The obtained results under the test conditions basically meet the standards of those with steady force test of models with high angle of attack in high speed wind tunnel.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2016年第8期2594-2602,共9页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(91216203)~~
关键词
风洞试验
边条机翼
动态特性
大迎角
数据精度
wind tunnel test
hinged strake-wing
dynamic performance
high angle of attack
data precision
