一种边条三角翼布局的纵向特性数值模拟  

Numerical Simulation on Longitudinal Characteristics of a StrakeDelta Wing Configuration

作　　者：孟祥喆 赵志俊 苏晓东[1] MENG Xiang-zhe;ZHAO Zhi-jun;SU Xiao-dong(Chinese Flight Test Establishment,Xi’an 710089,China)

机构地区：[1]中国飞行试验研究院,陕西西安710089

出　　处：《工业技术创新》2018年第6期25-29,43,共6页Industrial Technology Innovation

摘　　要：采用雷诺平均N-S方程(Reynolds-averaged Navier-Stokes,RANS),对一种边条三角翼布局进行CFD数值模拟,计算得到该布局的升阻特性、失速特性、纵向稳定性、纵向操纵性、前缘分离涡等情况。结果表明,该布局在小迎角范围内具有较为线性的升力曲线和力矩曲线,可通过线性拟合得到该机的气动力系数计算公式;超过一定迎角后,分离涡增升作用显著增强,升力线斜率增大,失速特性相比常规布局得到改善,但分离涡诱导的横向流动降低了升降舵效率。这种边条三角翼布局具有良好的气动特性,但应采用其它形式的舵面改善操纵性。In order to study the longitudinal characteristics of an aircraft with strake-delta wing configuration,CFD numerical simulation is carried out based on Reynolds-averaged Navier-Stokes(RANS)equation.The lift-drag characteristics,stall characteristics,longitudinal stability and maneuverability,and leading edge detached vortex at high angle of attack of such a configuration are calculated.The results show that this configuration has a relatively linear lift-line and torque-line within a range of low angle of attack,and the aerodynamic coefficient formula can be obtained by linear fitting.While beyond this range,the lift-line slope increases significantly,and the stall characteristics are improved compared with the conventional configuration.However,the lateral flow induced by the detached vortex reduces the control efficiency of elevator.Such a strake-delta wing configuration has good aerodynamic characteristics,but more effective elevator should be used to improve the maneuverability in engineering applications.

关 键 词：雷诺平均N-S方程 数值模拟 边条三角翼布局 升阻特性 失速特性 操纵性 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]