【摘要】：扇翼飛行器通過(guò)旋轉(zhuǎn)機(jī)翼前緣上部的橫流風(fēng)扇使扇翼飛行器同時(shí)獲得推力和高升力。由于升力和推力的產(chǎn)生都依賴于橫流風(fēng)扇旋轉(zhuǎn)在機(jī)翼弧形段內(nèi)形成的偏心渦,使得升力和推力之間有較強(qiáng)的耦合關(guān)系。單獨(dú)改變升力或者推力就變得十分困難,降低了扇翼飛行器的操縱性。經(jīng)過(guò)分析,扇翼機(jī)翼各幾何參數(shù)中前緣開(kāi)口角對(duì)氣動(dòng)性能的影響最大。通過(guò)在機(jī)翼前緣弧形段添加前緣小翼和開(kāi)槽,可以改變前緣開(kāi)口角的尺寸,從而改變來(lái)流進(jìn)入橫流風(fēng)扇的方向和流量,進(jìn)而改變扇翼的升力和推力,實(shí)現(xiàn)升推力的部分解耦。本文采用非定常數(shù)值模擬方法分析二維扇翼流場(chǎng),初步研究了前緣小翼及前緣開(kāi)槽對(duì)扇翼氣動(dòng)特性的影響。具體研究?jī)?nèi)容如下:本文首先介紹了國(guó)內(nèi)外對(duì)扇翼氣動(dòng)性能分析的研究現(xiàn)狀;其次,建立基于Navier-Stokes方程的扇翼氣動(dòng)性能分析的數(shù)值模擬方法,該方法采用分區(qū)網(wǎng)格劃分技術(shù)、滑移網(wǎng)格技術(shù)和RNG k??湍流模型;采用該方法分析前緣開(kāi)口角、前緣弧形槽間隙、橫流風(fēng)扇葉片安裝角等對(duì)前緣小翼和前緣開(kāi)槽設(shè)計(jì)有影響的幾何參數(shù),建立基準(zhǔn)模型并設(shè)計(jì)小翼和開(kāi)槽尺寸;然后,對(duì)比基準(zhǔn)模型與前緣小翼對(duì)扇翼氣動(dòng)性能的影響,分析不同小翼安裝角、不同小翼數(shù)目對(duì)氣動(dòng)性能的影響;最后,對(duì)比基準(zhǔn)模型與前緣開(kāi)槽對(duì)扇翼氣動(dòng)性能的影響,分析開(kāi)槽尺寸、開(kāi)槽數(shù)目、開(kāi)槽位置對(duì)扇翼氣動(dòng)性能的影響,得出了一些有意義的結(jié)論。
[Abstract]:The fan-wing aircraft obtains both thrust and high lift by rotating the crossflow fan at the top of the leading edge of the wing. Because the generation of lift and thrust depends on the eccentric vortex formed by the rotation of crossflow fan in the arc section of the wing, there is a strong coupling relationship between lift and thrust. Changing lift or thrust alone becomes very difficult, reducing the maneuverability of fan-wing aircraft. Through analysis, the front edge opening angle has the greatest influence on the pneumatic performance among the geometric parameters of the fan wing. By adding the leading wing and slotting to the arc section of the leading edge of the wing, the size of the opening angle of the leading edge can be changed, and the direction and flow rate of the incoming flow into the crossflow fan can be changed, and then the lift and thrust of the fan can be changed to realize the partial decoupling of the lifting thrust. In this paper, the non-steady numerical simulation method is used to analyze the flow field of two-dimensional fan wing, and the influence of front edge small wing and front edge slotting on the aerodynamic characteristics of fan wing is studied. The specific research contents are as follows: firstly, the research status of fan aerodynamic performance analysis at home and abroad is introduced. Secondly, the numerical simulation method of fan wing aerodynamic performance analysis based on Navier-Stokes equation is established, which adopts partition grid division technique, slip grid technique and RNG k? The turbulence model is used to analyze the geometric parameters which have influence on the slotting design of the leading wing and the leading edge, such as the opening angle of the leading edge, the arc slot clearance of the leading edge and the installation angle of the cross flow fan blade, and the reference model is established and the size of the wing and slotted is designed. Then, the influence of the reference model and the leading edge wing on the aerodynamic performance of the fan wing is compared, and the effects of different installation angles and the number of small wings on the pneumatic performance of the fan wing are analyzed. Finally, the influence of the reference model and the leading edge slotting on the aerodynamic performance of the fan wing is compared, and the effects of slotting size, slotting number and slotting position on the aerodynamic performance of the fan wing are analyzed, and some meaningful conclusions are obtained.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2015
【分類號(hào)】：V211

【引證文獻(xiàn)】

相關(guān)期刊論文 前1條

1 林超希;張文宇;馬超;;一種兩軸和四軸扇翼飛行器的設(shè)計(jì)[J];科技風(fēng);2017年13期

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本文編號(hào)：2491043