机翼风洞试验模型CFD静气动弹性修正研究

在低速增压风洞和跨声速风洞中,变雷诺数试验常用增压来实现。速压变化带来弹性变形的不同,造成伪雷诺数效应,其影响与雷诺数效应在同一量级。数值模拟了F4机翼在某低速增压风洞中的变雷诺数和变迎角试验。研究了其静气弹效应随迎角和风洞试验速压的变化规律。论证了对于风洞试验静气弹变形造成的伪雷诺数效应采用CFD方法修正的可行性。结果表明:对F4这种金属材料的中等展比后掠机翼,沿展向挠度和剖面扭转角等变形参量与迎角呈正相关。但迎角越大,增长幅度越小。随风洞试验速压也是正相关增长,但是等幅线性的。结合CFD技术进行风洞静气弹修正的方法是可行的。未来在如NASA研制的"太阳神"飞机等大展弦比、大柔性飞机的设计和风洞试验修正中将得到广泛应用。

Static Aeroelastic Correction for Wind Tunnel Results of Wing Model with CFD

Based on static aeroelasticity theory,the aeroelasticity behavior of F4 wing in pressurized wind tunnel is simulated numercially to analyze the influence of the elastic deformation on the model’s aerodynamic characteristics.The rules how bend deflection,twist angle change with wind tunnel experimental dynamic pressure or angles of attack are investigated.The results show that: typical sweptback wing,like F4 Wing,lead to the elastic equivalent angles of attack becoming smaller and lift coefficient decreasing.The bend deflection and twist angles of attack are positive linear with wind tunnel experimental dynamic pressure,and increase with angles of attack nonlinear.In conclusion,it is feasible to correct static aeroelasticity effect with CFD in wind tunnel experiments.Though the advantage is not evidence with such rigid wing,it will be widely used on high aspect ratio and high flexibility wing.