| 1. | Numerical simulation of turbulent flow field supersonic inlet
超声速进气道湍流流场的数值模拟 |
| 2. | Numerical simulation of turbulent flow in 2 - d mixed - compression supersonic inlet
二元混压超音速进气道湍流流场数值模拟 |
| 3. | The structure design and the performance research of supersonic inlet / combustor are key techniques for solid rocket ramjet
超声速进气道及补燃室的设计与性能研究是固体火箭冲压发动机的两大关键技术。 |
| 4. | The performance of supersonic inlet determines the pressure and the air flux in combustor , then affect the work of ramjet
超声速进气道的性能优劣决定了补燃室流场内的压强和空气流量,进而影响到冲压发动机的工作性能。 |
| 5. | Complex wave structures of supersonic inlet at critical status are achieved by numerical simulation , and analysis on flow structure characteristic and shock wave structure is made
得到了临界工况下超声速进气道内外粘性流场复杂的波系结构，分析了流场结构特性和激波波系结构。 |
| 6. | The full flow field characteristics of a supersonic inlet are illustrated at design conditions ; the influence of attack angle on flow field of the inlet is investigated ; b - spline theory is used to model the inlet with attack angle
给出了设计状态下进气道内外流场特征；分析了攻角变化对进气道流场的影响；以数值仿真结果为基础，利用b样条理论建立了反映攻角、马赫数及可调斜板角度变化的超声速进气道数学模型。 |
| 7. | On the study of supersonic inlet optimization algorithm , first , the inlet performance curve is converted to facilitate curve interpolation . then , with this converted performance curve , inlet optimization problem is converted to a simple nonlinear constrained optimization problem
在对超音速进气道进行优化时，首先对进气道特性进行适当变换，然后利用变换后的特性，将进气道的优化问题转化为一个易于求解的单变量约束非线性优化问题进行求解。 |
| 8. | This thesis is aimed at the pilot study about the integrated flow field of inlet and combustor , which is based on the optimized design and the performance analysis of supersonic inlet , in order to provide theoretical basis and direction for extension of flight enveloping and improvement of the synthetic performance of ramjet
本文的主要目的即是对超声速进气道进行优化设计和性能分析,并以此为基础开展超声速进气道/补燃室流场一体化的初步研究,为拓宽固体火箭冲压发动机的工作范围、提高其综合性能提供理论依据和指导。 |
| 9. | The main performance parameters of 2 - d ex - internal compression supersonic inlet have been calculated by means of the numerical simulation method , then the relations of these parameters and some factors , such as flight condition , geometric configuration parameters have been analyzed and summarized in this paper
本文通过数值模拟二元混压式超声速进气道的流场，计算并分析了飞行条件、几何结构等因素对进气道主要性能参数的影响，总结归纳了它们之间规律性的关系，研究了超曲面拟合方法。 |
| 10. | In this paper , two - dimensional and three - dimensional flow models in supersonic inlet and a simple reacting flow model in combustor and integrated flow field are established on the basis of k ? two - equation turbulence model and steady - compressible n - s equations , which are dispersed by finite volume method
本文以定常可压缩n - s方程作为控制方程,采用-双方程模型作为湍流模型,分别建立了超声速进气道的二维、三维流场计算模型和补燃室及一体化流场的湍流燃烧模型,并采用有限体积法对控制方程进行离散。 |
