| 1. | Numerical simulation of transonic flow field in two turbine cascades
两个涡轮叶栅跨声速流场的数值模拟 |
| 2. | On comparing flutter characteristics of three supercritical airfoils in transonic flow
超临界翼型的跨声速颤振特性研究 |
| 3. | Computation of wing flutter for unsteady transonic flows in the frequency domain is studied in this thesis
本文研究了机翼跨音速颤振的频域计算方法。 |
| 4. | Numerical simulation of 3d flow field in vki transonic cascade is presented to verify the algorithm ' s ability of simulating transonic flow , the result confirms it ' s applicability
为了考核现在的算法对跨音流场的模拟能力，数值模拟了vki跨音透平叶栅的三维流场，证明了该方法的可用性。 |
| 5. | 2 . the transonic flow field solutions of a ttcp standard waf - body combinations are computed using the software of cfd , the results are agreement with experiment dates , this verifies that the accuracy of the numerical simulation model is ensured
2 .应用cfd软件对某ttcp标准卷弧翼-身组合体跨声速下流场进行数值计算,将计算结果与文献试验结果进行对比,验证本文数值计算模型。 |
| 6. | Furthermore , numerical simulations for steady or unsteady transonic flow of rae2822 and dfvlr - r2 supercritical airfoils and a supercritical wings are investigated . the numerical results are in good agreement with experimental data where available
进而，应用该解算器对超临界翼型rae2822 、 dfvlr - r2及某超临界机翼的定常或非定常流场进行了数值计算研究，得出了良好、合理的结论。 |
| 7. | This deforming method coupled with ale euler solver is applied to simulate unsteady transonic flow about oscillating airfoil ( 2 - d ) and oscillating rigid rectangular wing ( 3 - d ) . computational results are in good agreement with experimental data
本文将网格变形方法与数值解算器耦合起来求解了二维振动翼型绕流和三维振动矩形机翼绕流，计算结果与实验结果一致，证明本文的数值方法具有较高的准确性。 |
| 8. | In this paper based on the optimization design method using control theory for airfoils , a design method for multi - element airfoils is developed with the chimera grids . and optimization computation for reducing drag of shockwave of single airfoil in transonic flow is also successful
本文的主要工作是：以在控制理论进行单段翼型优化设计的基础上，利用嵌套网格技术将其发展为适用于带襟翼多段翼型的优化设计。 |
| 9. | High - resolution nnd scheme and fully implicit dual - time stepping method were adopted in the three - dimensional vibrating cascade flow calculation . thus , the correct simulation of the shock in transonic flow and the efficiency of calculation were both taken into consideration
在三维振动叶栅流动数值模拟中，采用高分辨率tvd类型的格式和全隐式双时间方法，保证了对流动的正确模拟，准确地捕捉了跨音流动中的激波，其计算效率非常高。 |
| 10. | For unsteady - state calculations , jameson ' s dual - time method is used . to confirm the validity , effectivity and reliability of developed flow solvers based on ausm + scheme , test cases of steady / unsteady transonic flow of naca0012 airfoil and onera m6 wings are investigated first
本文首先以naca0012翼型、 oneram6机翼为算例，验证了本文发展的基于ausm +格式的跨音速定常、非定常navier - stokes euler方程解算器是正确、有效和可靠的。 |
