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在考虑各种影响因素的基础上，增加了交叉惯性积对稳定尾旋的影响，从而导出了分析稳定尾旋的有关公式。为了避免遗漏解的可能性，采用不需选择初值的求解方法，给出了稳定尾旋的判据。应用该方法对某型飞机的尾旋进行了预测计算，求出了一个陡尾旋解和一个平尾旋解，计算结果与该飞机尾旋试飞结果吻合较好，表明计算方法是正确的，计算结果可用于指导飞机的尾旋试飞。
Based on the various influencing factors, the influence of cross inertial product on the stable rotation is increased, and the relevant formulas for analyzing the stable rotation are derived. In order to avoid the possibility of omission of solution, the criterion of stable spin is given by using the solution without initial value selection. The method is applied to the prediction of the tail rotation of a certain type of aircraft. A steep-tailed spin solution and a horizontal tail solution are obtained. The calculated results are in good agreement with the results of the tail-flight test. It shows that the calculation method is correct. The results can be used to guide the aircraft’s tail spin test.