supersonic transverse injection 超声速横侧射流
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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。
Due to the smaller Angle of injection, the ratio of total pressure loss of aerodynamic ramp is less than the physical ramp and transverse injection stream.
由于喷流方向与主流方向夹角较小，总压损失也较物理斜坡、横向喷流等混合增强方式小。
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