流体机械
流體機械
류체궤계
FLUID MACHINERY
2010年
2期
31-34
,共4页
李常%梁武科%金雪红%王学涛
李常%樑武科%金雪紅%王學濤
리상%량무과%금설홍%왕학도
k-wSST湍流模型%翼型厚度%气动性能%非定常%分离流
k-wSST湍流模型%翼型厚度%氣動性能%非定常%分離流
k-wSST단류모형%익형후도%기동성능%비정상%분리류
k-w SST turbulence model%aerofoil thickness%aerodynamic performance%separated flow
在Re=3×10~6下,基于k-w SST两方程湍流模型对两种不同厚度的NREL风力机专用翼型进行了数值模拟,重点研究了-5°～15°攻角下不同厚度对翼型气动特性的影响规律.非定常计算结果表明:不同厚度对翼型气动性能影响显著,在某一小攻角范围,较小厚度值可获得较大升阻比,在大攻角翼型发生失速时,较大厚度值可提高翼型的升阻比,拓宽高升阻比的攻角范围,有效改善翼型的分离流动特性.
在Re=3×10~6下,基于k-w SST兩方程湍流模型對兩種不同厚度的NREL風力機專用翼型進行瞭數值模擬,重點研究瞭-5°～15°攻角下不同厚度對翼型氣動特性的影響規律.非定常計算結果錶明:不同厚度對翼型氣動性能影響顯著,在某一小攻角範圍,較小厚度值可穫得較大升阻比,在大攻角翼型髮生失速時,較大厚度值可提高翼型的升阻比,拓寬高升阻比的攻角範圍,有效改善翼型的分離流動特性.
재Re=3×10~6하,기우k-w SST량방정단류모형대량충불동후도적NREL풍력궤전용익형진행료수치모의,중점연구료-5°～15°공각하불동후도대익형기동특성적영향규률.비정상계산결과표명:불동후도대익형기동성능영향현저,재모일소공각범위,교소후도치가획득교대승조비,재대공각익형발생실속시,교대후도치가제고익형적승조비,탁관고승조비적공각범위,유효개선익형적분리류동특성.
Based on the k-w SST turbulence model , two airfoils of different thickness are simulated at Re=3×10~6, the aerodynamic characteristics of airfoil with different thicknesses at the attack angle of -5°～15° are investigated.The unsteady numerical results show that :the effect of the different aerofoil thickness is obvious to the aerodynamic performance ,at a small angle of attack range ,the greater thickness leads to the large lift-drag ratio ,at large angle of attack ,larger thickness can improve the lift-drag ratio,broaden the scope of the angle of attack of the high lift-drag ratio ,effectively improve the flow separation characteristics.
