本文選題：尾渦流場(chǎng)　切入點(diǎn)：數(shù)值模擬　出處：《中國(guó)民航大學(xué)》2015年碩士論文

【摘要】：隨著航空業(yè)的不斷發(fā)展,現(xiàn)有的尾流安全間隔偏大,已經(jīng)不能滿足空中交通流量增長(zhǎng)的需求。為此,本論文將尾流中對(duì)飛行安全影響最大的尾渦進(jìn)行深入研究,為縮小尾流間隔提供理論基礎(chǔ)。本論文主要通過流體力學(xué)研究方法中最經(jīng)濟(jì)快捷高效的數(shù)值模擬方法,利用ANSYS軟件中流體力學(xué)分析模塊,對(duì)尾渦流場(chǎng)的形成機(jī)理進(jìn)行研究,以揭示近場(chǎng)尾渦流場(chǎng)特性。首先用渦粘模型中S-A模型、k-ωSST模型和Realizable k-ε模型,分別對(duì)NACA0012二維翼型在不同馬赫數(shù)、不同迎角下的擾流以及NACA0012三維平直翼型的尾渦流場(chǎng)進(jìn)行數(shù)值模擬計(jì)算,并將預(yù)測(cè)結(jié)果與風(fēng)洞實(shí)驗(yàn)結(jié)果進(jìn)行對(duì)比,分析三種數(shù)值模擬方法的優(yōu)劣和模擬尾渦流場(chǎng)的準(zhǔn)確性,揭示尾渦流場(chǎng)的形成機(jī)理。最后對(duì)有無翼尖渦擴(kuò)散器的簡(jiǎn)易民航后掠翼模型分別進(jìn)行數(shù)值模擬計(jì)算,進(jìn)而對(duì)比分析翼尖渦擴(kuò)散器對(duì)尾渦的影響。經(jīng)過表面靜壓系數(shù)分布、升力系數(shù)曲線、極曲線、渦量、渦粘性、流線以及流場(chǎng)圖的比較分析,得出結(jié)論:Realizable k-ε模型在數(shù)值模擬尾渦流場(chǎng)方面效果最佳;翼尖渦擴(kuò)散器在改善翼尖處的升力分布的同時(shí),通過分流流經(jīng)翼尖的氣流,將翼尖渦打散成方向不同的四個(gè)渦,以此減弱尾渦強(qiáng)度和尾流范圍。
[Abstract]:With the continuous development of aviation industry, the existing wake safety interval is too large to meet the increasing demand of air traffic flow.Therefore, the wake vortex, which has the greatest influence on flight safety, is studied in this paper, which provides a theoretical basis for reducing the wake interval.In this paper, the formation mechanism of tail-vortex field is studied by using the most economical, fast and efficient numerical simulation method of hydrodynamic research method and the hydrodynamic analysis module in ANSYS software to reveal the characteristics of near-field tail-vortex field.Firstly, the S-A model and Realizable k- 蔚 model are used to simulate the turbulence field of NACA0012 two-dimensional airfoil at different Mach numbers and angles of attack, respectively, and the eddy-current field of NACA0012 three-dimensional flat-straight airfoil is simulated by using S-A model and Realizable k- 蔚 model respectively.By comparing the predicted results with the experimental results of wind tunnel, the advantages and disadvantages of the three numerical simulation methods and the accuracy of simulating the tail-vortex field are analyzed, and the formation mechanism of the tail-eddy current field is revealed.Finally, the airfoil vortex diffuser is numerically simulated, and the influence of the wingtip vortex diffuser on the wake vortex is compared and analyzed.Through the comparison and analysis of surface static pressure coefficient distribution, lift coefficient curve, polar curve, vorticity, eddy viscosity, streamline and flow field diagram, it is concluded that: realizable k- 蔚 model has the best effect in numerical simulation of tail vortex field.The tip vortex diffuser not only improves the lift distribution at the airfoil tip, but also disperses the wingtip vortex into four vortices in different directions by diverting the airflow through the airfoil tip, so as to weaken the wake intensity and wake range.
【學(xué)位授予單位】：中國(guó)民航大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2015
【分類號(hào)】：V211.4

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本文編號(hào)：1718992