| 1. | Numerical method on unstructured hybrid grid for hypersonic flows with magnetic fields
非结构混合网格高超声速绕流与磁场干扰数值模拟 |
| 2. | On the mathematical simulation of non - equilibrium hypersonic flow around the flying vehicle
关于飞行器高超声速不平衡气体绕流的数值模拟 |
| 3. | Taking advantage of hypersonic panel method , the analysis predicts lateral jet aerodynamic interaction for a blunted body in a hypersonic flow
将高超声速面元法用于喷流流场计算，计算结果与试验结果大体一致。 |
| 4. | Through the paper " s study , the cell - centred finite volume algorithm and the 2 - order ausm + finite volume algorithm can solve the subsonic flow problem well ; the nnd finite volume algorithm and 2 - order ausm + finite volume algorithm can solve the hypersonic flow problem well
研究表明，对于跨音速问题，格心以及二阶ausm +格式解决的很好；对于高超声速问题， nnd和ausm +格式解决的很好。 |
| 5. | The improved ausmwk scheme was extended on the three - dimensional flow field . three complicated 3d flow which included a supersonic flow at the comer of the intersecting wedges , a hypersonic flow in the lifting - body configuration and a flow in the rotating frame were numerically simulated by using ausmwk . results showed that the improved scheme could predict the complex turbulent flow more effectively than the original one .
通过与实验数据的比较，数值结果详细、准确地揭示了这几个复杂流场的流动现象，证实了ausmwk格式的改进是成功的，发展的ausmwk格式继承了ausm +格式优点，计算处理问题能力增强，可以有效地应用于亚声、跨声和高超声流动的工程实际问题中。 |
| 6. | 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。 |
| 7. | Using the engineering methods of supersonic and hypersonic flow or local piston theory developed in this paper to compute unsteady aerodynamic loads , and coupling structural equations , the supersonic or hypersonic aeroelasticity with a typical servo system under thermal environment is simulated in time - domain
运用超音速、高超音速气动力工程计算方法和本文发展的当地流活塞理论计算非定常气动力，耦合结构运动方程，实现了热环境中带有伺服机构的气动弹性的时域仿真。 |
