大型民用飞机模型Ф5m立式风洞尾旋特性试验研究

Free-spin Test in Φ5m Spin Tunnel for Large Civil Aircraft Model

为了研究某常规布局(大展弦比、后掠翼、翼吊式发动机)大型民用飞机的尾旋特性,制作了一个满足动力相似准则的无动力缩比模型,在Ф5m立式(尾旋)风洞中首次进行了大型民用飞机模型在不同构型、不同重心位置、不同重量、模拟不同飞行高度条件下的尾旋研究试验。试验结果表明,这架飞机的尾旋特性良好,模型在尾旋运动中比较稳定,旋转方向不发生改变,且旋转速度较慢。采用反舵(到底)推杆(到底)法可以满足所有状态下的尾旋改出,模型最快能够在不超过1/2圈或1s中改出。此种改出方法操作简便,是一种适合于大型民用飞机的尾旋改出方法。通过反尾旋伞试验确定了最佳的反尾旋伞参数。

An unpowered dynamic similarity scaled aircraft model under different conditions, such as different configurations, different centre of gravity locations, different weight, different simulated flight altitude, was tested in Ф5m vertical （spin） tunnel in first time to investigate the spin characteristics of a large civil aircraft （large as- pect ratio, backward sweep wing, wing mounted engine）. The results show that the spin characteristic of this air- craft was quite favorable. The spin motion of aircraft model was quite stable. Rotation direction of the model was not changed in spin motion, and rotation rate was quite low. The best spin recovery technique was to fully reverse rudder and fully forward the stick simultaneously, quickest recovery of the spinning model was within 1 second or no more than half circle. This spin recovery technique is Moreover, the most favorable parameters of the anti-spin easy to operate, which is suitable for large civil aircraft parachute was obtained by model free-spin tests.