某复杂构型飞机偏航-滚转耦合运动非定常气动力特性实验研究

摘要

A new set of double degree of freedom in volatile test system is designed and con-structed in FL-8 wind tunnel.The test apparatus can not only simulate aircraft′s single degree of freedom maneuver,but also realize yaw-roll coupling movement and pitch-roll coupling move-ment around the body axis.This paper introduces the experimental proj ect in detail and conducts research into the time history influence when the model is maneuvering.Afterwards the influence of the coupling factor on the unsteady aerodynamic characteristics undergoing yaw-roll coupling oscillation motion is analyzed quantitatively at the oscillation equilibrium position.The results in-dicate that the unsteady aerodynamic gained undergoing yaw-roll coupling oscillation motion is e-qual to the linear superposition of the unsteady aerodynamic gained in the test of single yaw and roll motions when the angle of attack at the equilibrium position is less than the stall angle of at-tack.The influence of the coupling factor on the unsteady aerodynamic is remarkable near the stall angle of attack.The influence of the coupling factor on the unsteady aerodynamic is weak when the angle of attack at the equilibrium position is much greater than the stall angle of attack.%在 FL-8风洞中设计并制造了一套双自由度大幅振荡实验系统，不仅能模拟飞机单自由度机动历程，还能实现模型绕体轴的偏航-滚转耦合运动及俯仰-滚转耦合运动。本文通过适当的实验设计，基于运动时间历程的影响分析，在振荡平衡位置定量地研究耦合因素对偏航-滚转耦合振荡运动中非定常气动力特性的影响。结果表明，当振荡运动平衡位置迎角远小于失速迎角时，偏航-滚转耦合运动的气动力等于单自由度运动相应气动力的线性叠加，平衡位置迎角在失速迎角附近时，非定常气动特性受耦合因素影响显著，而平衡位置迎角在远大于失速迎角时，非定常气动特性受耦合因素影响变小，但仍然较大。