本文通过喷管流场计算，附面层分离计算和传热计算说明试车中出现的现象。
The phenomenon appeared in these tests can be explained through the calculations of the nozzle flow field, boundary layers...
本文通过喷管流场计算，附面层分离计算和传热计算说明试车中出现的现象。
The phenomenon appeared in these tests can be explained through the calculations of the nozzle flow field, boun…
首先，考虑变化压力，分析微喷管流场各项参数的变化，得出其对微喷管性能的影响。
First, the influences of inlet pressure variations on micro nozzle's performance are obtained by analyzing the variations of various flow parameters in micro nozzle accordingly.
本文介绍了在低速射流风洞上开展的二维喷管来流带旋涡的模拟实验。
In the paper were carried out experiments on two-dimensional nozzle flow with and without incoming swirling in a low-speed wind tunnel.
基于实验数据和数值模拟结果，研究了外界反压和底部二次流对塞式喷管底部的影响。
Based on experimental data and numerical simulation results, effects of ambient pressure and base bleed on aerospike nozzle base behaviour are investigated.
本文介绍了超音速引射喷管的流场和性能的理论计算方法。
This paper presents an analytical method for calculating the flow field and performance of supersonic ejector nozzle.
通过测量固体火箭发动机水下工作过程中的推力和侧向力，研究了扰流片和摆喷管两种推力矢量方式的水下推力矢量特性。
By measuring the thrust and lateral forces of solid rocket motor during firing conditions, the thrust vector control performances of jet TAB TVC and movable nozzle TVC were studied.
从NS方程出发，采用二阶精度的NND格式对塞式喷管的流场进行了数值模拟。
The numerical simulations of the flow field around and aerospike nozzle cell were completed base on N S equations with Second order NND scheme.
用有限元素法数值模拟了固体火箭发动机喷管内缝隙的流场和热环境。
The flow field and thermal environment of gap in solid rocket nozzle were simulated by finite element method.
喷管中的气流由主流燃气和次流空气组成，用以模拟涡扇发动机的喷管。
The nozzle flow is composed of the main gas stream and the secondary air stream in order to simulate the nozzle of turbofan engine.
给出了典型的试验曲线，并分析了“瓦”状塞式喷管的高度特性和底部二次流对性能的影响情况。
The typical experimental curves are showed. The altitude characteristic and the effect of base bleed on aerospike nozzles are analyzed too.
利用特征线方法数值模拟了双圆弧和抛物线两种特型喷管中的三维非对称定常等熵的超音速流场。
Numerical simulation of three-dimensional, steady, isentropic, non-symmetrical flow in rocket nozzles is completed using a bicharacteristic method.
本文对小扩张比喷管内的两相流场进行了数值模拟。
This paper has simulated two-phase flow in a small expansion ratio nozzle.
声压级在相交激波点附近出现剧烈变化，喷管出口处的激波和排气羽流造成强噪声。
The sound pressure level changes acutely in shock intersection, and shocks outside nozzle and exhaust plume cause strong noise.
采用数值分析方法分析了跨声速喷管无粘流动和超声速射流对挡流板的冲击流场。
Numerical analyses of the transonic nozzle inviscid flow and supersonic jet impingement on a jet TAB are presented.
最后，非定常流的结果进一步表明，逆流喷管是一种较高效率的射流式矢量喷管。
Lastly, the results of unsteady flow point out, counterflow thrust vectoring nozzle is a efficiency fluidic vectoring nozzle.
尤其是喷管平衡流的计算方法文中作了详细的阐述。
The calculating method of equilibrium flow in nozzle is described ein detail.
采用SIMPL E算法的可压缩形式求解固体火箭发动机燃烧室喷管内的全速度统一流场；
United flow field at all flow speeds in the chamber and nozzle of SRM is solved by using the compressible form of the SIMPLE algorithm.
研究了一次流参数和二次喷管结构对引射效能和发动机推力的影响，找到了逐步提高推力的措施。
The influence of primary flow and secondary nozzle geometry on ejector effect and thrust was investigated, and the approach to increase thrust of rocket ejector was found gradually.
最后，本文针对两种构型的超音速尾喷管，对其流场进行了计算和分析。
In final section of this paper, the flow field of two types of supersonic nozzle for scramjet is simulated and analyzed.
在分析喷管内气体的流动时，假设工作气体是完全的理想气体，气体的流动是等熵位流。
An assumption is made that the exhaust gas is perfectly ideal, and the gas flow within the nozzle is isentropic.
采用收敛扩张喷管，使雾化区形成高压而又连续流动的流场，是高压下雾化试验研究的好方法。
The key feature of the experiment is to use a convergent-disvergent nozzle to maintain a high air pressure in the test chamber and at the same time t…
本文对旋转固体火箭发动内的两相流场进行了数值模拟，主要目的是研究燃烧室—喷管内气相和颗粒相在旋转情况下的流动特性。
Two-phase flow field of spinning solid rocket motor is simulated, and gas-particle of two-phase is analyzed in this paper.
然后，利用某型号固体火箭发动机进行喷管分离流试验，测得了喷管壁面上沿轴向的压强分布数据。
Then, the experiment of flow separation in the nozzle was done with a solid rocket motor, and the inside pressure data along the axis of the nozzle was gotten.
所述喷管具有朝金属表面引导液体制冷剂流和蒸气流的罩盖。
The lance has a hood that directs both a flow of liquid cryogen and a flow of vaporous gas toward the metal surface.
次流压比的增加将导致激波向扩张段上游移动，且喷管矢量角不断增加；
Along with the increase of the secondary flow pressure ratio, the shock move toward upstream divergent section and the thrust vector angle gradually increases;
在分析喷管内气体的流动时，假设工作气体是完全的理想气体，气体的流动是等熵位流。
An assumption is made that the exhaust gas is perfectly ideal, and the gas flow within the...
采用STAR - CD计算流体软件对某俄式发动机的喷管内流场及喷管出口处流场进行了三维的数值仿真与研究。
Numerical 3d simulation and research on inner nozzle and outlet flow field of solid rocket motor of long range missile designed by Russia using STAR-CD computational fluid software.
试验结果表明：主喷管直径和旋流槽尺寸是影响供油特性的主要因素；
The results show that the main -nozzle diameter and the size of swirl slots are contributing factors to the fuel supply characteristics;
试验结果表明：主喷管直径和旋流槽尺寸是影响供油特性的主要因素；
The results show that the main -nozzle diameter and the size of swirl slots are contributing factors to the fuel supply characteristics;
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