A Study on Airfoil Design for Future Mars Airplane
A Study on Airfoil Design for Future Mars Airplane
复制标题
未来火星飞机翼型设计研究
DOI：
10.2514/6.2006-1484
复制
发表时间：
2006
期刊：
影响因子：
--
通讯作者：
K. Fujii
中科院分区：
文献类型：
--
作者：
A. Oyama;K. Fujii
采用进化计算和二维reynolds -average Navier-Stokes求解相结合的方法，得到了未来火星探测飞机的最佳翼型设计。并将优化后的翼型设计与其他不同雷诺数和不同马赫数优化后的翼型设计进行了比较，讨论了雷诺数和马赫数对翼型设计的影响。结果表明：1)升阻最大化意义下的最佳翼型厚度分布较薄；2)最佳弧度分布取决于设计工况的雷诺数和马赫数；3)最佳前缘形状取决于设计工况的雷诺数。
An optimum airfoil design for future Mars airplane for Mars exploration is obtained by evolutionary computation coupled with a two-dimensional Reynolds-averaged Navier-Stokes solver. The optimized airfoil design is also compared with other airfoil designs optimized at different Reynolds number or at different Mach number to discuss Reynolds number and Mach number effects on airfoil design. The present results indicate 1) optimum airfoil shape in the sense of maximization of lift-to-drag has thin thickness distribution, 2) Optimum camber distribution depends on both Reynolds number and Mach number of the design condition, 3) Optimum leading edge shape depends on Reynolds number of the design condition.