摘要
采用空间二阶精度的交替方向隐式分解的NND格式求解完全气体假定下的非定常薄层近似Navier Stokes方程 ,并采用抛物化的椭圆型方程生成复杂带翼外形的空间网格。最后给出带控制舵机动弹头在M∞ =7 3,α =2 0°下所计算的流场等值线。
Under the assumption of perfect gas,the thin layer N S equations are solved by alternating direction implicit NND scheme,and the space grids of complex wing shape are generated by solving parabolic partial differential equations. Finally,the numerical simulation results of maneuvering missile with the control helm are shown under the conditions:M ∞=7 3,α=20°. The results include contours of flow field, pressure distribution and limiting streamline along the surface.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2002年第3期1-3,共3页
Journal of National University of Defense Technology
基金
国家部委基金资助项目 (4 13 13 0 10 1)
湖南省自然科学基金资助项目 (0 1JJY2 0 0 8)
