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本文给出了求位于弹翼后的安定面升力特性的近似方法,该方法适用于当安定面的翼展大于弹翼翼展的情况(见图1),从工程的角度获得解决,并且最终的结果以便于实际使用的形式给出。在飞行器气动力设计过程中初步计算时,所得的结果可在M=0～2的范围内使用。
This paper gives an approximate method for determining the lift characteristics of a stabilizer located behind a wing. The method is suitable for solving the problem when the span of the stabilizer is greater than that of the wing span (see Figure 1), and the final solution The result is given in a form that is actually used. The initial results of the aerodynamic design of the aircraft can be used in the range of M = 0 ~ 2.