摘要
应用第二代面元法对发动机短舱的压强分布进行了计算。计算结果表明其精确度与第一代高阶面元法相当;并可避免第一代面元法计算内流时出现的“泄漏”(leakage)问题。该方法具有节省机时和便于复杂外形应用的特点。
In the process of aerodynamic design, the panel method is one of the main computing tools. In this paper the second generation low order panel method is used for calculation of the pressure distribution on the nacelle in low speed. It is demonstrated that the present low order method gives comparable accuracy to the result of high order panel method, It is excellent compared with some earlier low order methods, e.g. 'the leakage' in internal flows calculation does not appear with the present method. Meanwhile, the computing cost of the method is very low and it is very easy for application to complex configurations.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1993年第6期B299-B302,共4页
Acta Aeronautica et Astronautica Sinica
基金
上海民用飞机技术研究中心部分资助
关键词
面元法
短舱
不可压流动
panel method, nacelle, incompressible flow
