| 1. | Effect of inlet - air velocity distribution on performance of evaporative condenser
来流流场对蒸发式冷凝器性能影响的研究 |
| 2. | The simulation results were studied the interaction mechanisms among burning jet flow and upstream flow were demonstrated
分析和比较了模拟结果，揭示了空气来流和燃气射流对弹箭的干扰机理。 |
| 3. | The equal density and pressure of free streams are chosen to study the effect of compressibility on the mixing layer
计算选取来流密度和压力相等，对流马赫数从0 . 2到1 . 2 ，以研究压缩性对混合层流动的影响。 |
| 4. | It shows that the model has a good agreement for single - supply alluvial experiment . but the model is n ' t suit for multiple alluvial experiment
由于缺乏合理的多次堆积模式，对于泥石流多次来流的累加堆积情况不适用。 |
| 5. | The experimental results show that the gridding rib has significant effects on heat transfer enhancement . the nuselts number increases as re increases
实验结果表明，网格式内冷通道中，随着来流雷诺数re的增加，通道换热效果增强。 |
| 6. | This demonstrates that for propulsion - airframe integration , this genus of inlet would be advantageous in keeping the stability of boundary layer coming from the forebody
一体化设计时，该进气道对保持前机体来流附面层的稳定性十分有利。 |
| 7. | The flows of pipes in the different conditions with the significant stimulations are solved . the results obtained are analyzed and compared to experimental results referred to
求解了不同形状管道，不同来流条件下，非微小激励情况下的管内流的流场。 |
| 8. | On basis of this solution , the influence of flow to the vibrating pipe is analyzed and the method of obtaining resonant frequency and resonant time are given
之后，根据此解，对来流雷诺数的影响进行了分析，并给出了求解、分析共振频率及共振时刻的方法。 |
| 9. | The effect of area ratio , mach number , total pressure of primary rocket and geometry structure of primary rocket on ejectorjet performance was studied
通过数值计算研究了引射火箭堵塞比、来流马赫数、一次火箭燃烧室总压、一次火箭构型对引射火箭性能的影响。 |
| 10. | The results indicated with the re raising , the rectangle channel ' s heat transfer enhanced gradually , which channel installed the baffle on its above and below
实验结果表明，上下壁面安装折流板的矩形通道中，随着来流雷诺数re的增加，通道换热效果逐步增强。 |
