摘要
本文采用Glerkin有限元方法以全位势方程为控制方程计算了航天机三维简化模型的亚声速流动。为模拟实际流动,在后部加一尖劈形后体,并施出一尾涡面。为局部超声速区解的稳定,采用人工密度修正。对密度和环量进行双重迭代,得到了亚声速下三维航天机的压力分布和气动力系数。
The subsonic flow of three-dimensional simplified space shuttle geometry is calculated by galerkin finite element method. The Governing equation is based on the full potential equation. A sharp wedge shape after-body and tail vortex sheets are added to simulate actual flow. An artificial density correction is used for the stability on local supersonic region. The iterations of density and circulation are carried out. The pressure distributions and aerodynamic coefficient of the subsonic flow for three-dimensional space shuttle are given.
出处
《上海力学》
CSCD
1999年第3期229-234,共6页
Chinese Quarterly Mechanics
