| 1. | These thrust losses may be very large if the inlet flow distortion is in the order of 15 to 20 percent .
若进口流场的畸度在15-20范围内的话，则推力损失就可能十分巨大。 |
| 2. | Research on the measures to improve inlet flow pattern for multi - sets pumping station with side - inlet
侧向进水多机组泵站进水流态改善措施研究 |
| 3. | Impact of the shape of the hull back of amphibious vehicle on the inlet flow field of waterjet propulsion
两栖车辆车体尾部形状对喷水推进器进口流场的影响 |
| 4. | The results show that those two modifications have certain impact on the inlet flow field
计算结果显示，这两项措施对风机进口处流场的改善起到了一定的作用。 |
| 5. | These thrust losses may be very large if the inlet flow distortion is in the order of 15 to 20 percent
若进口流场的畸度在15 - 20范围内的话，则推力损失就可能十分巨大。 |
| 6. | The effect of exit back pressure and length / height ratio of isolator on forebody / inlet flow field is analyzed and discussed in the paper
本文还研究了隔离段出口反压及隔离段长高比对进气道流场的影响。 |
| 7. | The simulation code for the calculation of inlet flow is developed based on various models using dsmc method , through the simulation of micro - scale flow of various working conditions , we get the flow properties of the micro - scale
通过对大量不同工况的微流动过程进行仿真,研究了微尺度喷管的流动特性,同时验证了本文所建模型的有效性。 |
| 8. | The numerical simulation of the inlet flow fields in the gas turbine . obtained numerical simulation results of flow fields include the uniformity , with the geometrical boundary completely according with the actual one and nothing being simplified
在几何边界形状上严格反映物理真实而不作任何简化，获得了整个进气系统地流场分布状况和压气机进口截面的不均匀度。 |
| 9. | 2 - d , axisymmetric , and sidewall compression scramjet inlets flow fields are calculated and the performance of each inlet is analyzed . configurations of generic sidewall compression scramjet inlets are introduced and two kinds of spillage are introduced respectively
然后对二维压缩、轴对称压缩和侧压式进气道的性能进行了计算,分析了进气道在设计状态和非设计状态的性能。 |
| 10. | The stability will fall when inlet flow is distorted . a circumferential critical distorted angle exists in the compressor , the stability of the compressor will change little when circumferential distorted angle is greater than critical distorted angle
进气畸变会使压气机的稳定性下降，但压气机存在一周向临界畸变角，当进气周向畸变区域大于周向临界畸变角时，压气机的稳定裕度和在临界畸变角时的相比，变化很小。 |
