【摘要】 基于分离涡模拟(DES)方法及平流上游分割方法(AUSM)格式,利用Fluent软件对偏转头弹箭在零攻角和不同偏转角时的超声速流场和气动参数进行了数值模拟。比较偏转头弹箭和普通弹箭的流场结构发现,二者头部激波结构差异较大,但下游流场几乎相同;该流场结构提高了弹箭的气动特性。偏转头对气动力系数的影响主要表现为增加弹箭头部的升、阻力系数,且升力系数增量大于阻力系数。在零攻角情况下,偏转头弹箭具有一定升力,该升力可有效降低维持其飞行高度所需的驱动力,提高偏转弹的机动性。更多还原

【Abstract】 Based on the detached eddy simulation and the advection upstream splitting method(AUSM)scheme,the supersonic flow field and aerodynamic force coefficients of a projectile with the deflectable nose are simulated numerically under the condition of zero angles of attack and deflection angles using the Fluent software. Through the comparison of the flow structures of projectiles with and without deflectable noses,the structures of shock wave are finded to be different greatly at the forebody of the projectile and the flow fields of the downstream of the forebody are almost the same. The result shows that the deflectable nose can improve the aerodynamic characteristics of the projectile. Under the condition of zero angles of attack,the deflectable nose can generate the aerodynamic lift and it can reduce the thrust keeping the projectile flying at certain height and improve its maneuvering.更多还原