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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。
In order to meet the requirements of aerodynamic performance evaluation, precise control system design and high maneuverability targets of a new generation of high-maneuverable aircraft, it is imperative to explore the pitch dynamic characteristics of the high-speed wind tunnel and determine the accuracy of experimental data. Important engineering significance. The 70 ° delta wing model, SDM and Su-27 aircraft models were selected to study the dynamic aerodynamic characteristics and experimental data accuracy in FL-24 wind tunnel with large amplitude and pitch dynamic test technology platform. The 70 ° delta wing model, Dynamic Aerodynamic Characteristics and Repeatability Test Results of SDM and Su-27 Aircraft Models. The results show that under the experimental conditions, the dynamic data accuracy of the three models is high, and the accuracy of conventional force test data at high angle of attack of high-speed wind tunnel is basically reached.