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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。
In order to study the tail rotation characteristics of a large commercial aircraft of a conventional layout (large aspect ratio, swept-wing wing, wing-hang engine), a powerless reduction model satisfying the power similarity criterion was made. For the first time in a wind tunnel, large-scale civil aircraft model in different configurations, different center of gravity position, different weight, simulation of different flight altitude spin test research. The experimental results show that this aircraft has good tail rotation characteristics, the model is stable in the wake rotation, the rotation direction does not change, and the rotation speed is slow. With the anti-helm (in the end) putter (in the end) method to meet the tail spinout in all states, the model can be rewound in no more than 1/2 turn or 1 second. This method is easy to change out is a tail rotation suitable for large civil aircraft out of methods. The best paraxial parachute parameters were determined by anti-spin-parasol test.