摘要
用Osher格式求解三维、可压缩流动方程组 ,计算和分析了某火炮膛口气流现象。在建立差分算法时 ,将有限体积离散和黎曼解算器相结合 ,简化了计算工作。首先 ,以楔形风洞中马赫数为Ma∞=2 .0的超音速流动问题开展数值实验 ,数值结果与理论值吻合很好 ;其次 ,计算了火炮膛口气流问题 ,取得包括炮车表面等位置的膛口全流场的流动参数分布 。
The three-dimensional compressible flow equations were solved using the Osher's scheme. The flow phenomena of a gun's muzzle were calculated and analyzed. In the construction of difference algorithm, the work of calculation is simplified by the combination of the finite volume discretization method and Riemann's solver. Firstly, the numerical test of the supersonic flow through a wedged wind tunnel at Mach number Ma infinity = 2.0 was done. The numerical results agree well with the theoretical analysis. Secondly, the gun's muzzle flow problem was calculated. The flow parameter distributions of the whole flow-field around the muzzle including the carriage surface were obtained and the flow process was described in detail.
出处
《兵工学报》
EI
CAS
CSCD
北大核心
2004年第1期19-22,共4页
Acta Armamentarii
关键词
火炮
膛口流动
冲击波
流体力学
数值计算
fluid mechanics, gun, muzzle flow, shock wave, numerical calculation
