通航飞机高升力层流机翼优化设计
发布时间：2019-03-23 19:11
【摘要】：为了扩展机翼优化设计的工程应用范围,在传统气动优化约束的基础上,考虑结构布置的几何约束,对通用飞机层流机翼进行了设计。首先,采用自由变形(FFD)技术作外形参数化处理;然后,采用NSGA-Ⅱ多目标优化算法,基于Kriging代理模型对某型通用飞机机翼进行了优化设计。设计过程考虑自然转捩工况,采用Menter k-ωSST两方程湍流模型和γ-Re_(θt)转捩模型对设计进行评估。计算结果表明,优化后机翼的巡航和爬升升阻比均有所提高、层流区延长、低头力矩变小,但最大升力系数减小了0.141,失速特性略有变差。
[Abstract]:In order to extend the engineering application of wing optimization design, a general aircraft laminar flow wing is designed on the basis of traditional aerodynamic optimization constraints and geometric constraints of structural layout. First, the free deformation (FFD) technology is used to parameterize the shape, and then the NSGA- 鈪，
本文编号：2446144
[Abstract]:In order to extend the engineering application of wing optimization design, a general aircraft laminar flow wing is designed on the basis of traditional aerodynamic optimization constraints and geometric constraints of structural layout. First, the free deformation (FFD) technology is used to parameterize the shape, and then the NSGA- 鈪，
本文编号：2446144
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