CAJ | 학술논문

基于 NREL S809翼型，研究尾翼摆角对于翼型气动性能的影响。通过对比升阻力系数的模拟值与实验值，排除了网格质量对翼型气动性能的影响，验证了利用 S－A（Spalart-Allmaras）湍流模型对风力机翼型进行计算的有效性，确定了合理的模拟方案，分析了翼型的气动性能。在此基础上，将 S809翼型进行了尾缘变形，生成 S809上摆－5°、下摆5°、10°及15°这4种变形翼型。再利用CFD （computational fluid dynamics）软件对它们进行数值计算，分析了各个翼型升阻力系数及流场特性。研究表明，随着尾缘下摆角度的增加，变形翼型上下表面压差逐渐增大，下摆翼型在升阻力特性方面有较大改善。但随着翼型下摆角度的增大，翼型产生分离涡的攻角却随之减小，更易失速。而上摆翼型升阻力特性及失速特性均不如原始翼型。
기우 NREL S809익형，연구미익파각대우익형기동성능적영향。통과대비승조력계수적모의치여실험치，배제료망격질량대익형기동성능적영향，험증료이용 S－A（Spalart-Allmaras）단류모형대풍력궤익형진행계산적유효성，학정료합리적모의방안，분석료익형적기동성능。재차기출상，장 S809익형진행료미연변형，생성 S809상파－5°、하파5°、10°급15°저4충변형익형。재이용CFD （computational fluid dynamics）연건대타문진행수치계산，분석료각개익형승조력계수급류장특성。연구표명，수착미연하파각도적증가，변형익형상하표면압차축점증대，하파익형재승조력특성방면유교대개선。단수착익형하파각도적증대，익형산생분리와적공각각수지감소，경역실속。이상파익형승조력특성급실속특성균불여원시익형。
NREL S809 airfoil was selected as an object to study the impact of trailing edge angle on its aerodynamic performances.The simulation results were compared with the experiment ones to rule out the grid quality effects on aerodynamic performance,the effectiveness of S-A (Spalart-Allmaras)turbulence model was verified and a reasonable simulation scheme was made sure to analyze the airfoil well and truly.On this basis,the S809 trailing edge swing angle was altered to generate S809 -5°,5°,10°,15°deformed airfoils.Then the CFD software was used to analyze numerically each airfoil’s aerodynamic characteristics.With the increase of trailing edge swing angle,the differential pressure on the upper and lower surfaces of the airfoil becomes bigger.So for the positive swing angle airfoils the lift and resistance characteristics are improved,however,when the airfoil swing angle is increased,the angle of attack becomes smaller and the separation vortex would appear.For negative swing angle airfoils,all of the lift,resistance and stalling characteristics are worse.