摘要
对典型的大展弦比和中等展弦比机翼在0．7～0．9马赫数区间进行了串行和并行计算的数值校验，证实了以N—S（Navier—Stokes）方程为主控方程的串行和并行流场求解器的正确性，并讨论了并行效率和加速比．结合Powell算法，讨论了在确定的机翼平面形状和翼型的条件下，以升阻比最大为目标的三维机翼截面翼型最大厚度与扭角的优化设计．算例结果表明，厚度的非线性分布和负的扭角会改善机翼流场的流动状态，使机翼的升阻比得到提高，优化设计方法是可行的．
The serial and parallel flow field solution program was validated at two Mach numbers between 0.7 and 0.9 using both a high and a moderate aspect ratio wings. The result based on the Navier-Stokes（N-S） equations proved it right and the parallel efficiency as well as speed-up ratio was discussed. With the goal of maximizing lift-to-drag ratio, the optimization of three-dimensional wing＇s section thickness and twist angle was discussed. N-S equations as flow field sovler and Powell method were used as design tools, and the wing＇s aspect shape was fixed. The subcritical parallel computation case and supercritical serial computation case dem- onstrated that nonlinear distribution of thickness and negative twist angle could ameliorate the condition of flow field around the wing, which lead to a higher lift-to-drag ratio. The optimization method is effective.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2008年第2期127-130,共4页
Journal of Beijing University of Aeronautics and Astronautics
基金
国家自然科学基金资助项目(10472013)
航空科学基金资助项目(04A51044)
关键词
优化设计
机翼设计
N—S方程
并行计算
optimization design
wing design
navier-stokes equations
parallel computation
