本文選題：風(fēng)力機(jī) + 翼型��； 參考：《南京航空航天大學(xué)》2014年碩士論文

【摘要】：針對對S809翼型的靜態(tài)和動態(tài)性能、以及PHASE VI葉片在三維旋轉(zhuǎn)流場的氣動性能，本文采用CFD方法開展數(shù)值模擬研究和分析。主要研究內(nèi)容包括： 對S809二維翼型靜態(tài)性能問題，在計(jì)算過程中，使用了4種湍流模型對S809翼型進(jìn)行了全湍流模擬，發(fā)現(xiàn)SST k-ω湍流模型的模擬效果與實(shí)驗(yàn)結(jié)果最為接近。但是大迎角狀態(tài)下，S-A模型和k-ε模型預(yù)測的氣流分離點(diǎn)較實(shí)驗(yàn)值靠后，導(dǎo)致升力顯著高于實(shí)驗(yàn)值。之后又比較了SSTk-ω湍流模型模擬的翼型幾個狀態(tài)下的表面壓力分布和流場結(jié)構(gòu)，研究了翼型靜態(tài)失速下的氣動性能。 對S809二維翼型動態(tài)性能問題，，計(jì)算得到了翼型動態(tài)失速下的升阻力遲滯曲線，并分析了翼型在典型狀態(tài)下的表面壓力分布與流場結(jié)構(gòu)，研究S809翼型的動態(tài)失速特性。模擬結(jié)果表明，該模擬結(jié)果和之前靜態(tài)性能的模擬的結(jié)論是一致的，并得到了翼型升阻力系數(shù)的遲滯曲線。不過由曲線可以看出，翼型進(jìn)入失速的臨界攻角較大，這和之前實(shí)驗(yàn)的結(jié)果略有出入，這可能是全湍流模擬的弊端，在之前進(jìn)行翼型靜態(tài)性能模擬的時候就已經(jīng)發(fā)現(xiàn)了。 對NREL PHASE VI三維葉片進(jìn)行了旋轉(zhuǎn)流場的數(shù)值模擬，得到了一些葉片的基本性能。和實(shí)驗(yàn)結(jié)果比較發(fā)現(xiàn)，F(xiàn)luent的模擬結(jié)果從定性上能夠準(zhǔn)確模擬出PHASE VI風(fēng)力機(jī)葉片隨著風(fēng)速增大進(jìn)入失速和深失速的整個狀態(tài)，在葉片失速前和深失速后的模擬結(jié)果和實(shí)驗(yàn)吻合良好，但對于臨界攻角的預(yù)測上比實(shí)驗(yàn)結(jié)果靠后，從而導(dǎo)致了失速段的模擬和實(shí)驗(yàn)值有一定的偏差，這和之前對二維翼型的模擬結(jié)論相一致。
[Abstract]:Aiming at the static and dynamic performance of S809 airfoil and the aerodynamic performance of PHASE VI blade in three-dimensional rotating flow field, the CFD method is used to carry out numerical simulation and analysis in this paper. The main research contents include: For the static performance of S809 two-dimensional airfoil, four turbulence models are used to simulate the full turbulence of S809 airfoil. It is found that the simulation effect of SST k- 蠅 turbulence model is the closest to the experimental results. But the gas separation points predicted by the S-A model and the k- 蔚 model at high angle of attack are lower than the experimental values, and the lift force is significantly higher than the experimental value. Then the surface pressure distribution and flow field structure of airfoil simulated by SSTk- 蠅 turbulence model are compared, and the aerodynamic performance of airfoil under static stall is studied. For the dynamic performance of S809 two dimensional airfoil, the rising drag hysteresis curve is obtained under the dynamic stall of the airfoil. The surface pressure distribution and flow field structure of the airfoil under typical conditions are analyzed, and the dynamic stall characteristics of S809 airfoil are studied. The simulation results show that the simulation results are consistent with those of the previous static performance simulation, and the hysteresis curves of the lift resistance coefficient of the airfoil are obtained. However, it can be seen from the curve that the critical angle of attack of airfoil entering stall is large, which is slightly different from the results of previous experiments. This may be the disadvantage of full turbulence simulation, which has been discovered in the previous static performance simulation of airfoil. The rotating flow field of NREL PHASE VI three dimensional blade is numerically simulated and the basic performance of some blades is obtained. Comparing with the experimental results, it is found that the simulation results of fluent can accurately simulate the whole state of PHASE VI wind turbine blade entering stall and deep stall with the increase of wind speed. The simulation results before and after the blade stall are in good agreement with the experiment. However, the prediction of critical angle of attack is later than that of the experimental results, which leads to a certain deviation between the simulated and experimental values of the stall section, which is consistent with the previous simulation results for two-dimensional airfoils.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2014
【分類號】：TM315

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