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基于DES(detached eddy simulation,分离涡模拟)方法及AUSM(advection upstream splitting method,对流迎风分裂方法)格式,对不同偏角的偏转头弹箭在非零攻角下的超声速流场和气动特性进行了数值模拟.结果表明:在非零攻角情况下,与常规弹箭流场相比,偏转头弹箭头部迎风面激波更强;而当有效入射角相等时,即使弹箭的攻角不一样,其头部流场结构仍相同,且尾翼流场基本不受头部偏角影响.另外,由气动力系数变化曲线可知,偏转头弹箭具有良好的纵向静稳定性,且升力系数随攻角的增长率大于阻力系数,即升阻比大于常规弹箭,因此适当增大攻角可以提高偏转头弹箭的气动特性.
Based on the detached eddy simulation (DES) and the advection upstream splitting method (AUSM), the supersonic flow field and aerodynamic characteristics of the deflected-head projectile with different declination angle under a non-zero angle of attack The numerical results show that, compared with the conventional missile flow field, the windward shock wave of the deflector head is stronger than that of the conventional missile. When the effective incident angles are equal, The angle of attack is not the same, the structure of the head flow field is still the same, and the tail flow field is basically not affected by the declination of the head.In addition, the curve of the aerodynamic coefficient shows that the deflection head has excellent longitudinal static stability, And the rate of increase of the lift coefficient with the angle of attack is greater than the drag coefficient, that is, the lift-drag ratio is larger than the conventional missile. Therefore, appropriately increasing the angle of attack can improve the aerodynamic characteristics of the deflector.