But total pressure loss increases with the increasing of the velocity difference accompanied with the increase of the density and the static temperature ratio.

但速度差随密度比、静温比增大而增大时总压损失亦随之增大。

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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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At the end of the annular passage, shock wave occurs when the relative lift is less than 6% and the pressure ratio is less than 0.7, which causes a greater total pressure loss.

在相对升程小于6%、压比小于0.7后，环形通道的末端将产生激波，激波带来较大的全压损失。

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