摘要
针对某民机翼身组合体加装不同翼梢小翼——融合式翼梢小翼和翼尖涡扩散器进行对比分析。用软件ICEM生成原始翼身组合体及加装不同小翼的翼身组合体的点对点对接多块网格技术生成高质量的数值计算网格,运用Roe三阶迎风偏置通量差分裂方法和隐式近似因子分解方法求解雷诺平均N-S方程。对两种不同翼梢小翼在巡航点进行数值模拟,得到合理的翼稍小翼几何参数;对比升阻特性数据,两种翼梢小翼都可以提高升力系数,减少阻力系数。相对原始翼身组合体,融合式翼梢小翼升阻比增加9%,翼尖涡扩散器升阻比增加6%;但翼尖涡扩散器在力矩特性上有较大优势。所得结论对民用飞机翼稍小翼设计工作具有较大的工程应用价值。
A certain type of civil aircraft wing and body are equipped with two different forms of winglets-Fusion Winglet and tip-fence.The point-to-point patched multi-block technology was used to generate high quality grid by ICEM software.Three-dimensional time-dependent compressible Reynolds-averaged Navier-Stokes equations were solved with third-order upwind-biased flux-difference splitting method and approximate factorization method.The numerical simulation was adopted to obtain reasonable geometry parameters of two different winglets at cruise point.The result data indicates that both winglet has increased lift coefficient and decreased drag coefficient,compared with the original wing-body model.The fusion winglet increased the lift to drag ratio by 9%,and the tip fence increased the lift to drag ratio by 6%.However,the advantage of wing-body equipped with tip-fence in moment characteristic is obvious.The conclusions have great engineering application value in the design of civil aircraft winglet.
出处
《航空计算技术》
2011年第1期38-43,共6页
Aeronautical Computing Technique
基金
国家自然科学基金资助项目(10772148)
