摘要
对民用客机上使用较多的两种翼尖装置(融合式翼梢小翼和翼尖涡扩散器)进行了对比分析与研究。在基本机翼参数相同的基础上,利用ICEM软件对基本机翼及分别加装两种不同翼尖装置的机翼生成点对点对接的高质量多块结构化计算网格,采用Roe三阶迎风偏置通量差分裂方法和隐式近似因子分解法求解耦合SA湍流模型的雷诺平均Navier-Stokes方程。通过计算得知:在巡航状态下分别加装融合式小翼和翼尖涡扩散器后,两种机翼的升阻比分别提高了10.945%和4.993%,俯仰力矩系数分别增加了9.410%和5.116%,翼根弯矩系数分别增加了7.380%和1.013%。分析结果表明:相比于翼尖涡扩散器,融合式翼梢小翼能更显著地提高机翼的升阻比,但同时也较为明显地增加了机翼的俯仰力矩和翼根弯矩,从而导致飞机配平阻力和翼根结构重量的增加。
Two kinds of widely used wingtip devices in civil transport,blended winglet and vortex diffuser,are thoroughly analyzed and compared with each other.The point to point patched multi-block technology is used to generate high quality structured grid by ICEM software.Three-dimensional time-dependent compressible Reynolds-averaged Navier-Stokes equations coupled with SA turbulence model are solved with third-order upwind-biased flux-difference splitting method and approximate factorization method.After the installation of blended wingtip and vortex diffuser,the lift-drag ratio of the two wings are increased by 10.9445% and 4.993% under cruising status,with increase of 9.410% and 5.116% in pitching moment coefficient and increase of 7.380% and 1.0133% in wing-root bending moment coefficient.Numerical results obtained suggest that,compared to vortex diffuser,the blended winglet has higher increase for lift-drag ratio,pitching moment and wing-root bending moment,which leads to the increase of trim drag and wing-root structure mass.
出处
《应用力学学报》
CAS
CSCD
北大核心
2013年第4期498-503,643,共6页
Chinese Journal of Applied Mechanics
基金
国家自然科学基金(10802066)
