Fuselage shape optimization of a wing-body configuration with nacelles
Fuselage shape optimization of a wing-body configuration with nacelles
复制标题
带短舱的翼身结构的机身形状优化
DOI：
10.2514/2.3093
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发表时间：
2001
影响因子：
2.2
通讯作者：
Z. Lei
中科院分区：
文献类型：
--
作者：
Y. Makino;T. Iwamiya;Z. Lei
开发了一种将计算流体动力学代码与最小阻力优化技术相结合的气动设计工具，并将其应用于一架1.7马赫比例超音速实验飞机的机身形状优化。考虑到机身/机舱的集成。将优化后的机身与采用线性理论设计的轴对称面积直纹机身进行了比较。结果表明，采用非轴对称机身设计理念，采用该优化设计工具可有效降低压阻，尤其适用于机身与机舱间产生较强干扰阻力的飞机设计。
An aerodynamic design tool that combines a computational e uid dynamics code with an optimization technique for a drag minimization is developed and applied to a fuselage shape optimization of a Mach 1.7 scaled supersonic experimental airplane. An airframe/nacelle integration is taken into consideration. The optimized fuselage is compared with a conventional axisymmetrical area-ruled fuselage designed by a lineartheory. The results indicate that a nonaxisymmetrical fuselage design concept with this optimization design tool iseffectivefor the reduction of pressuredrag,especially inthedesign ofan airplanethatgeneratesa strong interferencedrag between itsairframe and nacelles.