CAJ | 학술논문

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。
기우분리와모의( DES)방법급평류상유분할방법( AUSM)격식，이용Fluent연건대편전두탄전재령공각화불동편전각시적초성속류장화기동삼수진행료수치모의。비교편전두탄전화보통탄전적류장결구발현，이자두부격파결구차이교대，단하유류장궤호상동；해류장결구제고료탄전적기동특성。편전두대기동력계수적영향주요표현위증가탄전두부적승、조력계수，차승력계수증량대우조력계수。재령공각정황하，편전두탄전구유일정승력，해승력가유효강저유지기비행고도소수적구동력，제고편전탄적궤동성。
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.