CAJ | 학술논문

应用有限体积方法求解三维可压缩雷诺平均N-S方程,计算了巡航导弹外形飞行器作小振幅俯仰运动时的动态绕流流场和空气动力特性,开展了导弹绕不同转轴、以不同频率和在不同迎角范围内进行俯仰运动的非定常气动力迟滞特性研究.计算结果表明,当导弹作快速俯仰运动时,在上仰和下俯过程中的同一迎角瞬间,绕导弹流场流动明显不同,表现出明显的非定常迟滞特性.导弹的非定常气动力迟滞特性随俯仰运动频率的增大明显增强,且气动力迟滞曲线随着俯仰轴位置的变化而变化.在同一减缩频率下,导弹在不同迎角范围内作周期俯仰运动时,相同的运动相位角所对应的升力系数对迎角的导数是一致的,而不同减缩频率下升力系数对迎角的导数随运动相位角变化曲线明显不同.
응용유한체적방법구해삼유가압축뢰낙평균N-S방정,계산료순항도탄외형비행기작소진폭부앙운동시적동태요류류장화공기동력특성,개전료도탄요불동전축、이불동빈솔화재불동영각범위내진행부앙운동적비정상기동력지체특성연구.계산결과표명,당도탄작쾌속부앙운동시,재상앙화하부과정중적동일영각순간,요도탄류장류동명현불동,표현출명현적비정상지체특성.도탄적비정상기동력지체특성수부앙운동빈솔적증대명현증강,차기동력지체곡선수착부앙축위치적변화이변화.재동일감축빈솔하,도탄재불동영각범위내작주기부앙운동시,상동적운동상위각소대응적승력계수대영각적도수시일치적,이불동감축빈솔하승력계수대영각적도수수운동상위각변화곡선명현불동.
Numerical simulations for three-dimensional Reynolds averaged Navier-Stokes equations are carried out to predict the flowfield characteristics of a pitching winged missile based on the finite volume method.The Baldwin-Lomax eddy viscosity model with the modifications suggested by Degani and Schiff is used here.The computational results of the aerodynamic loads of a 76° swept delta wing with a pitching motion are also given,which are in good agreement with the experiment data.The unsteady aerodynamics about a winged missile,which oscillates in pitching with different frequencies,at different oscillating positions and at different range of angle of attack,are shown in this paper.It is found,from the computational results,that the unsteady hysteresis of the lift,the drag and the pitch moment coefficients vary not only with the frequency,but also with the position of the oscillating axis.When the missile oscillates in pitching within different ranges of the angle of attack,the derivative of lift coefficient with respect to the angle of attack is the same for the same phase of oscillation under the same reduced frequency condition.