【摘要】：針對(duì)跨聲速后掠翼,三維鼓包串作為一種有效的減阻方式具有結(jié)構(gòu)簡單、高效及魯棒性好等優(yōu)點(diǎn).利用全局優(yōu)化算法探索了鼓包設(shè)計(jì)參數(shù)空間的整體特性,并對(duì)鼓包長度、三維鼓包展向設(shè)計(jì)參數(shù)對(duì)鼓包減阻效果的影響進(jìn)行了研究,發(fā)現(xiàn)鼓包頂點(diǎn)位置和高度對(duì)阻力系數(shù)最敏感,三維鼓包的展向設(shè)計(jì)參數(shù)則對(duì)阻力系數(shù)不敏感,而鼓包長度和鼓包相對(duì)展長越長越有利于減阻.在此基礎(chǔ)上開展了小后掠角自然層流機(jī)翼加3種不同類型鼓包串的優(yōu)化研究,通過優(yōu)化結(jié)果發(fā)現(xiàn),增加優(yōu)化后的三維鼓包串,可將小后掠角自然層流機(jī)翼阻力發(fā)散馬赫數(shù)向后推移,并且鼓包平均長度和控制區(qū)越大,效果越好.三維鼓包串具有良好的局部控制特性,可用于局部較強(qiáng)激波的抑制.三維鼓包串對(duì)常規(guī)后掠翼波阻具有良好的控制效果,同時(shí)能夠抑制激波誘導(dǎo)的機(jī)翼后緣氣流分離.
[Abstract]:As an effective drag reduction method, three-dimensional drum string has the advantages of simple structure, high efficiency and good robustness. The global optimization algorithm is used to explore the overall characteristics of the drum design parameter space, and the effects of the drum length and the three-dimensional design parameters on the drag reduction effect are studied. It is found that the position and height of the top of the drum are the most sensitive to the drag coefficient, while the design parameters of the three-dimensional drum are not sensitive to the drag coefficient, while the length of the drum and the relative extension of the drum are more favorable to reduce the drag. On the basis of this, the optimization of three different types of drum strings for the natural laminar flow wing with small sweep angle is carried out. Through the optimization results, it is found that the optimized three-dimensional drum string is increased. The Mach number can be diffused from the natural laminar flow wing with small sweep angle, and the larger the average length of bulge and the larger the control zone, the better the effect is. The three-dimensional drum string has good local control characteristics and can be used to suppress local strong shock waves. The three dimensional drum string has a good control effect on the wave resistance of the conventional swept wing and can restrain the shock induced airflow separation at the rear edge of the wing.
【作者單位】： 中國空氣動(dòng)力研究與發(fā)展中心高速空氣動(dòng)力研究所;南京航空航天大學(xué)航空宇航學(xué)院;
【基金】：國家自然科學(xué)基金(11372337,91216203,10972233) 中央高�；究蒲袠I(yè)務(wù)費(fèi)專項(xiàng)科研項(xiàng)目(NS 2014013)
【分類號(hào)】：V211.4

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