Implementation of the panel method to the solution of flow around aircraft

INCAS Bulletin

Yassir ABBAS¹  Mohammed MADBOULI² 

[1] Aeronautical Engineering Department, Engineering College, Cairo University Giza State, Egypt [e-mail]*;Aeronautical Engineering Department, Engineering College, Cairo University Giza State, Egypt, [e-mail];

关键词: aerodynamics;    panel method;    influence matrix;    velocity potential;   

DOI  :  10.13111/2066-8201.2015.7.2.1

来源: DOAJ

【 摘 要 】

In this study a panel method is used as a numerical technique for the solution of the potential three dimensional flows about a complete aircraft configuration to determine the aerodynamic characteristics. This approach seems to be more economic, from the computational point of view than methods that solve the flow field in the whole fluid volume such as finite difference, finite element or finite volume techniques. A system of source and doublet distributions is implemented and Dirichlet boundary conditions are applied. A computer program using Matlab is developed. Firstly flow over three dimensional swept wings is solved and the results are compared with experimental data to validate the numerical panel code. After the ideas have been discussed a sample calculations around complete aircraft are presented to illustrate the gain of using panel method technique.

【 授权许可】

Unknown