首先推导了适用于某第三代超声速战斗机横航向运动方程和传递函数。
Firstly, the directional lateral motion equations and transfer functions suited for the certain third generation fighter were deduced.
通过对多个复杂超声速横侧射流工况的计算，验证了新模型的预测效果。
Several complex supersonic transverse injection flows were calculated to verify the performance of the new model.
通过对多个复杂超声速横侧射流工况的计算，验证了新模型的预测效果。
Several complex supersonic transverse injection flows were calculated to verify the performance of the new model.
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