Viscous transonic airfoil workshop compendium of results
Viscous transonic airfoil workshop compendium of results
复制标题
粘性跨音速翼型研讨会成果概要
DOI：
10.2514/3.45706
复制
发表时间：
1987
影响因子：
2.2
通讯作者：
T. Holst
中科院分区：
文献类型：
--
作者：
T. Holst
本文对1987年1月在美国内华达州里诺举行的AIAA第25届航空航天科学会议上举行的粘性跨音速翼型研讨会的结果进行了相互比较，并与实验数据进行了比较。在这个研讨会中使用的测试用例包括三种不同翼型的附着和分离跨音速流：NACA 0012翼型，RAE 2822翼型和琼斯翼型。共包括来自15个不同作者组的23组数值结果。使用的数值方法有很大的不同，包括：16种Navier-Stokes方法，2种Euler/边界层方法和5种全位势/边界层方法。结果表明，高度的复杂性之间的数值方法与一般良好的协议之间的各种计算和实验结果连接或适度分离的情况下。就较大分离的案件达成的协议只是公平的，并表明需要在这方面做更多的工作。
Results from the Viscous Transonic Airfoil Workshop held at the AIAA 25th Aerospace Sciences Meeting at Reno, NV in January 1987, are compared with each other and with experimental data. Test cases used in this workshop include attached and separated transonic flows for three different airfoils: the NACA 0012 airfoil, the RAE 2822 airfoil, and the Jones airfoil. A total of 23 sets of numerical results from 15 different author groups are included. The numerical methods used vary widely and include: 16 Navier-Stokes methods, 2 Euler/boundary-layer methods, and 5 full-potential/boundary-layer methods. The results indicate a high degree of sophistication among the numerical methods with generally good agreement between the various computed and experimental results for attached or moderately-separated cases. The agreement for cases with larger separation is only fair and suggests additional work is required in this area.