【摘要】：為了擴(kuò)展機(jī)翼優(yōu)化設(shè)計的工程應(yīng)用范圍,在傳統(tǒng)氣動優(yōu)化約束的基礎(chǔ)上,考慮結(jié)構(gòu)布置的幾何約束,對通用飛機(jī)層流機(jī)翼進(jìn)行了設(shè)計。首先,采用自由變形(FFD)技術(shù)作外形參數(shù)化處理;然后,采用NSGA-Ⅱ多目標(biāo)優(yōu)化算法,基于Kriging代理模型對某型通用飛機(jī)機(jī)翼進(jìn)行了優(yōu)化設(shè)計。設(shè)計過程考慮自然轉(zhuǎn)捩工況,采用Menter k-ωSST兩方程湍流模型和γ-Re_(θt)轉(zhuǎn)捩模型對設(shè)計進(jìn)行評估。計算結(jié)果表明,優(yōu)化后機(jī)翼的巡航和爬升升阻比均有所提高、層流區(qū)延長、低頭力矩變小,但最大升力系數(shù)減小了0.141,失速特性略有變差。
[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，

本文編號：2446144