NUMERICAL SOLUTION OF THE UNSTEADY EULER EQUATIONS FOR AIRFOILS USING APPROXIMATE BOUNDARY CONDITIONS  

作　　者：高超 罗时钧 刘锋 

机构地区：Department of Aircraft Engineering,Northwestern Polytechnicaf University,Xi'an 710072,China[1] Department of Mechanical and Aerospace Engineering, University of California, Irvine, CA 92697-3975, USA[2]

出　　处：《Acta Mechanica Sinica》2003年第5期427-436,共10页力学学报（英文版）

摘　　要：This paper presents an efficient numerical method for solving the unsteady Euler equations on stationary rectilinear grids. Boundary conditions on the surface of an airfoil are implemented by using their first-order expansions on the mean chord line. The method is not restricted to flows with small disturbances since there are no restrictions on the mean angle of attack of the airfoil. The mathematical formulation and the numerical implementation of the wall boundary conditions in a fully implicit time-accurate finite-volume Euler scheme are described. Unsteady transonic flows about an oscillating NACA 0012 airfoil are calculated. Computational results compare well with Euler solutions by the full boundary conditions on a body-fitted curvilinear grid and published experimental data. This study establishes the feasibility for computing unsteady fluid-structure interaction problems, where the use of a stationary rectilinear grid offers substantial advantages in saving computer time and program design since it does not require the generation and implementation of time-dependent body-fitted grids.

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]