Applicable range of this model and way for improving control surface efficiency have been pointed out.
指出数学模型的适用范围和改善操纵面效率的途径。
The analytical results indicate that the control surface efficiency analyzed based on nonlinear experimental aerodynamic forces and linear theoretical aerodynamic forces are different.
研究表明：使用非线性试验气动力和线性理论气动力所分析得到的舵面效率具有较大的差别；
An optimization method is used to obtain deflection Angle of control surface and the aerodynamic efficiency of airfoil is calculated.
用数值优化方法取得自适应翼型最优的舵面偏角，并计算其气动特性。
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