机翼前掠过程气动中心变化规律  

A Study of the Change Regulation of Aerodynamic Center with the Wing Sweeping Forward

作　　者：张冬[1] 胡孟权[1] 王旭[1] 吴章沅 

机构地区：[1]空军工程大学航空航天工程学院,西安710038

出　　处：《空军工程大学学报（自然科学版）》2015年第4期1-4,共4页Journal of Air Force Engineering University(Natural Science Edition)

基　　金：国家自然科学基金资助项目(11402301);航空科学基金资助项目(20110596007)

摘　　要：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。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 configuration executes corresponding missions, this makes an aerodynamic center moveable in a small scale.

关 键 词：变前掠翼 气动中心 有限体积法 前掠角 数值仿真 

分 类 号：V221[航空宇航科学与技术—飞行器设计]