CAJ | 학술논문

基于一种滑轨式变前掠翼布局飞行器，采用三维N??S控制方程的有限体积法离散格式，对不同状态下飞行器的气动中心进行数值计算，得到了变前掠翼布局飞行器气动中心的位置。在相同马赫数下，总结了变前掠翼布局飞行器气动中心随前掠角的变化规律；在相同前掠角下，总结了变前掠翼布局飞行器气动中心随马赫数的变化规律。通过机体表面压力云图以及机翼截面压力系数分布图，分析了变前掠翼布局飞行器气动载荷分布，总结了引起气动中心变化的原因。结果表明：在相同马赫数下，气动中心随前掠角的增大，先少量后移再较大前移；在相同前掠角下，随着飞行马赫数的增大，气动中心均向后移动，移动量在可接受范围内；选取合适的任务模式，可使气动中心仅在小范围移动。
기우일충활궤식변전략익포국비행기，채용삼유N??S공제방정적유한체적법리산격식，대불동상태하비행기적기동중심진행수치계산，득도료변전략익포국비행기기동중심적위치。재상동마혁수하，총결료변전략익포국비행기기동중심수전략각적변화규률；재상동전략각하，총결료변전략익포국비행기기동중심수마혁수적변화규률。통과궤체표면압력운도이급궤익절면압력계수분포도，분석료변전략익포국비행기기동재하분포，총결료인기기동중심변화적원인。결과표명：재상동마혁수하，기동중심수전략각적증대，선소량후이재교대전이；재상동전략각하，수착비행마혁수적증대，기동중심균향후이동，이동량재가접수범위내；선취합괄적임무모식，가사기동중심부재소범위이동。
In order to research the change regulation of aerodynamic center based on a variable forward??swept wing (VFSW)configuration with a slide way sweeping ,by adopting a format of N??S control equa-tions with the method of finite volume method,the aerodynamic center on the VFSW configuration under different conditions is numerically simulated,and the location of the aerodynamic center is obtained.The change regulation of aerodynamic center with the sweep angle in the same Mach number and the change regulation of aerodynamic center with Mach number at the same sweep angle are summarized.The corre-sponding reason is analyzed through surface pressure contour over configuration and pressure coefficient on the wing.The results show that the aerodynamic center moves backward slightly and then reverses heavily with the increase of sweep angle in the same Mach number.With the increase of flight Mach number,the aerodynamic center moves forward in a tolerance interval at the same sweep angle.When the VFSW con-figuration executes corresponding missions,this makes an aerodynamic center moveable in a small scale.