大展弦比机翼跨声速静气动弹性风洞试验

Wind tunnel test on transonic static areoelasticity of high-aspect-ratio wing

基于静气动弹性风洞试验研究了某翼身组合体的跨声速静气动弹性效应。试验结果表明:在设计巡航点,静气动弹性对大展弦比超临界机翼的气动特性影响明显,可使机翼的升力系数降低21%、升阻比增加8%、焦点前移约1%bA;在超过巡航马赫数后,静气动弹性效应使得机翼气动特性有恶化的趋势。跨声速时,马赫数和速压对机翼的静气动弹性效应具有较大影响,且影响规律呈复杂非线性,难以依据现有理论分析准确预计。

Static aeroelasticity has great influence on the aerodynamic performance and safety of aircrafts. Based on a wing-body model for aerodynamic/structural similarity, a static aeroelastic wind tunnel test was carried out to research the transonic static aeroelastic effects. The results show that the static aeroelasticity has significant influence on the aerodynamic performance for the hypercritical high-aspec--ratio sweepback wing at its designed cruise point. The static aeroelastic effects lead to 21 % decrement in the lift coefficient,8% increment in the lift-drag ratio,and the forward movement of the aerodynamic centre about 1 %bA. With the Mach number higher than the designed cruise value, the static aeroelastic effects worsen the wing, s aerodynamic performance. In addition, in transonic range, the Mach number and dynamic pressure have significant influence on the static aeroelastic effects？ and the influence has nonlinear characteristics. It is difficult to precisely predict the influence law and magnitude by current theory.