扇翼飞行器垂直升降可行性研究

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基于扇翼机的飞行原理，提出通过改变攻角以及增加尾部升力面弦长的方式提高气动效率，进而实现垂直升降的方法。通过建立扇翼飞行器的二维数学模型进行模拟分析、设计试验模型并进行了相关实验比较分析，证明垂直升降的可行性。研究结果表明，增加升力面弦长至原始长度的3倍之后，在无风或迎风风速较小情况下，攻角30°左右即可实现合力垂直向上，即实现垂直升降。

Based on the principle of flight of fan wing aircraft, realizing methods of VTOL are preposed by changing the angle of attack and increasing chord length of the tail. According to comparative analysis between the 2D mathematical model simulation and the of test model design of fan wing aircraft, the feasibility of VTOL is proven. Research results show that, after increasing the lifting surface chord length three times as much as the length of the original design, under the condition of no wind or lower wind velocity,30 degrees attack angle will achieve VTOL.

扇翼飞行器，数学模型，垂直升降，fan wing aircraft，mathematical model，VTOL。

扇翼飞行器垂直升降可行性研究。