These phenomena are controlled by the nature of the subsonic flow field.
这些现象也反映了燃烧室内亚音速流场的性质。
A special treatment is made in outlet boundary in which the subsonic and supersonic flow exist commonly. Block-Line-Gauss-Siedel method is used to solve THD differencing equations.
对离散方程采用线超松驰方法迭代求解，在亚音速与超音速气流共同存在的出口边界分情况进行了处理。
However, after the shock the flow in the jet will still be subsonic.
不过，后休克的流动，在射流仍会亚音速。
For several given types of inlet boundary layer, a numerical investigation on flow field of bowed stator vanes under two inlet subsonic Mach Numbers was carried out.
给定不同型式的进口边界层，在两种不同亚音速条件下对一平面扩压静叶栅的弯叶片流场进行了数值模拟。
The present article describes the pilot stand of a full scale ten-stage subsonic axial-flow compressor and presents the test results of the rotating stall and surge obtained therefrom.
本文介绍了一个全尺寸十级亚音速轴流压气机试验台，并给出了该实物压气机旋转失速和喘振的试验结果。
Subsonic vortical flows over a slender body at different angles of attack were simulated numerically, and the aerodynamic characteristics of asymmetric vortical flow were also investigated.
运用数值方法模拟了细长体在不同攻角条件下亚音速绕流的背涡结构，探讨了非对称涡流的气动力特性。
In this paper, the flow field of the supersonic diffuser and the subsonic-supersonic ejector is simulated by numerical method.
本文采用上述数值算法模拟了超声速扩压器和超声速引射器内流场。
Predicted drag values for a given airfoil(RAE2822 airfoil)were compared and discussed using the surface integration and wake integration methods under both subsonic and supercritical flow conditions.
在亚跨声速时分别采用了表面积分和尾迹积分求得给定翼型RAE2822的阻力。
The accuracy and realability of the numerical software used to simulate the flow field of subsonic compressor is verified by the experiment data of a certain low speed two stage repeated compressor.
采用低速重复级压气机实验数据，验证了本文所采用的数值方法模拟亚声速压气机流场的精度和可靠性。
In this paper, the accelerating feature of solar wind flow from subsonic and sub-Alfven velocity into supersonic and super-Alfven velocity is discussed in the axis-symmetric magnetic flux tube.
本文讨论了轴对称磁力线管中太阳风从亚声速和亚阿尔文速度加速到超声速和超阿尔文速度的过程。
The unsteady flow field near the leading edge of an oscillating sweptback wing is obtained by using 3-D subsonic lifting surface theory.
本文应用三元亚音速升力面理论求出了后掠翼前缘附近的流场。
The unsteady flow field near the leading edge of an oscillating sweptback wing is obtained by using 3-D subsonic lifting surface theory.
本文应用三元亚音速升力面理论求出了后掠翼前缘附近的流场。
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