| 1. | The area correction is largest at the nozzle exit, where it may be of the order of 3% .
面积修正在喷管出口处最大，约为3左右。 |
| 2. | Effects of preform structure on mechanical properties of carbon - carbon composite for nozzle exit cone
喷管出口锥材料力学性能的影响 |
| 3. | In order to separate gas and solid two phases completely , the velocity of particles at the exit of laval nozzle should be high enough , therefore the laval nozzle should be long enough
?了更好地实现气、固两相分离，颗粒在缩放喷管出口处的速度应该足够大，因而缩放喷管就应该足够长。 |
| 4. | The results show that to design a supersonic / hypersonic nozzle of wind tunnel must consider the effect of variable specific heat , which gives reference to nozzle and wind tunnel design
考虑这一因素后，喷管出口马赫数接近设计马赫数，其设计精度有较大提高。本方法可为超音速高超声速喷管设计和反设计提供参考。 |
| 5. | The conclusion that the optimal secondary nozzle exit area generating the maximum thrust agrees well with the numerical simulation , indicating that the exit area of secondary nozzle should be optimized according to structure and flow parameters during design
表明在引射火箭设计时，应结合引射火箭的结构和流动参数对二次喷管出口面积进行优化设计，以达到最佳推力性能。 |
| 6. | It is shown that with the decrease in size of particles , their velocity at the exit of laval nozzle increases under the conditions of both the invariable gas parameters and the same laval nozzle length ; the laval nozzle length increases with the size of particles under the same speeding rate of particles
研究表明，在气流参数和缩放喷管长度不变的情况下，被气流拖曳的颗粒越大，颗粒在缩放喷管出口处的速度就越低；在颗粒加速率相同的情况下，颗粒越大，所需的喷管长度就越长。 |
| 7. | The results indicate that with decrease of exit area of secondary nozzle , the bypass ratio is decreasing , and the static pressure in integrated ejector combustor is increasing , and mixing condition becomes better . there exists an optimal exit area of secondary nozzle to get maximum thrust of rocket ejector
结果表明：引射能力随着二次喷管出口面积的减小而减小；整体式引射燃烧室压强随着二次喷管出口面积的减小而上升，混合随之更为充分；存在一个最优的二次喷管出口面积，使发动机推力最大。 |
| 8. | It is shown that when the exit area of secondary nozzle and the fuel / oxidizer ratio is fixed , the increase of mass flow rate of secondary flow lead to the decrease of velocity of mixed flow , and increase of total mass flow rate . the synthetical result of these two phenomenon cause the increase of thrust of rocket ejector , but the increasing magnitude is relatively small , indicating that these is no necessary to claim large bypass ratio in rocket ejector design . in the comparison between two configurations , the typical one has better performance , indicating the importance of pressure ratio
结果表明：在固定二次喷管出口面积和氧燃比的条件下，二次流(引射空气流)流量的增加引起混合气体出口速度的下降和总流量的增加，二者综合作用使发动机推力增加，但增幅不大，表明在设计发动机结构和工作参数时，不必过分追求大的引射系数；两种结构的性能对比分析表明了增压比对引射火箭性能的提高具有重要意义；对引射火箭的热力循环分析同样表明，增压比对于提高发动机性能非常关键。 |
| 9. | To prove the accuracy of the mach number , and the parameter homogeneity of the design nozzle " s exit , cfd calculate has carried on the design results . under the condition of supersonic and hypersonic flow , and a certain range of temperature , and mach number , the conclusion of the influence of specific heat to nozzle design is drawn
为了验证所设计的喷管出口马赫数的大小和喷管出口流场的均匀性，采用nnd格式和b l湍流模型求解雷诺平均n - s方程，对设计结果进行了cfd验算，得出了在一定温度范围内，超音速、高超声速流动的条件下，不同马赫数范围内变比热容对喷管型面和喷管出口马赫数的影响。 |
| 10. | Abstract : optimum distances between primary nozzle exit and mixing tube inlet , static pressure recovery of the mixing flow in mixing tube 、 total pressure distributions at the exit of mixing tube 、 pumping coefficients and total pressure losses of the exhaust ejector systems with four different types of primary nozzles have been measured in the experiments
文摘:对4种主喷管组成的排气引射系统的引射系数和总压损失、各主喷管出口与混合管进口之间的最佳间距、混合气流在混合管内的静压恢复及混合气流在混合管出口处的总压分布等进行了测量和对比。 |
