实验流体力学
實驗流體力學
실험류체역학
Journal of Experiments in Fluid Mechanics
2015年
5期
1-7,25
,共8页
后退式 Mini-TED%翼型气动特性%低雷诺数%表面压力分布%PIV 测量
後退式 Mini-TED%翼型氣動特性%低雷諾數%錶麵壓力分佈%PIV 測量
후퇴식 Mini-TED%익형기동특성%저뢰낙수%표면압력분포%PIV 측량
rearward Mini-TED%aerodynamics of airfoil%low Reynolds number%surface pres-sure distribution%PIV measurement
介绍了装有后退式微型后缘装置（Rearward Mini-TED）的 NACA23012翼型在低雷诺数条件下的表面压力分布、气动力和 PIV 速度场的风洞实验结果，并与 NACA23012原型翼的对应测量结果进行了对比分析，以探讨 Mini-TED 装置对翼型流场、气动特性产生的影响。本实验风速为15m／s，以弦长为特征量的雷诺数为 Re ≈1．3×105，翼型表面压力分布采用测压孔和压力传感器测量，通过积分获得翼型升力和压差阻力，并利用尾耙测量翼型受到的总阻力。结果表明，后退式 Mini-TED 翼型改变了翼型周围的流场速度分布和尾流流动结构，导致上翼面吸力和下翼面的压力升高，使翼型升力增加，但压差阻力也增加。同时发现后退式 Mini-TED 翼型使前驻点位置后移，加快了上翼面的流动速度，后缘分离受到抑制。
介紹瞭裝有後退式微型後緣裝置（Rearward Mini-TED）的 NACA23012翼型在低雷諾數條件下的錶麵壓力分佈、氣動力和 PIV 速度場的風洞實驗結果，併與 NACA23012原型翼的對應測量結果進行瞭對比分析，以探討 Mini-TED 裝置對翼型流場、氣動特性產生的影響。本實驗風速為15m／s，以絃長為特徵量的雷諾數為 Re ≈1．3×105，翼型錶麵壓力分佈採用測壓孔和壓力傳感器測量，通過積分穫得翼型升力和壓差阻力，併利用尾耙測量翼型受到的總阻力。結果錶明，後退式 Mini-TED 翼型改變瞭翼型週圍的流場速度分佈和尾流流動結構，導緻上翼麵吸力和下翼麵的壓力升高，使翼型升力增加，但壓差阻力也增加。同時髮現後退式 Mini-TED 翼型使前駐點位置後移，加快瞭上翼麵的流動速度，後緣分離受到抑製。
개소료장유후퇴식미형후연장치（Rearward Mini-TED）적 NACA23012익형재저뢰낙수조건하적표면압력분포、기동력화 PIV 속도장적풍동실험결과，병여 NACA23012원형익적대응측량결과진행료대비분석，이탐토 Mini-TED 장치대익형류장、기동특성산생적영향。본실험풍속위15m／s，이현장위특정량적뢰낙수위 Re ≈1．3×105，익형표면압력분포채용측압공화압력전감기측량，통과적분획득익형승력화압차조력，병이용미파측량익형수도적총조력。결과표명，후퇴식 Mini-TED 익형개변료익형주위적류장속도분포화미류류동결구，도치상익면흡력화하익면적압력승고，사익형승력증가，단압차조력야증가。동시발현후퇴식 Mini-TED 익형사전주점위치후이，가쾌료상익면적류동속도，후연분리수도억제。
The pressure distribution,aerodynamics and PIV velocity fields of a NACA23012 airfoil mounted with a rearward Mini-TED captured in a low speed wind tunnel tests are intro-duced and compared with experimental results of a NACA23012 prototype airfoil in this paper,in order to investigate the influence of the Mini-TED to the flow field and aerodynamics loads of the airfoil.The Reynolds number is 1.3×10 5 based upon the chord length of the airfoil.The pressure distribution on the airfoil is measured using the pressure tubes and pressure transducers,and then the results are integrated to obtain the lift force and pressure drag acting on the airfoil.The total drag is measured using the comb of stagnation pressure based on the momentum theorem. The velocity fields around the airfoil are captured by a PIV system.The rearward Mini-TED in-duces changes to the flow velocity around the airfoil and the wake flow structure,which leads to the variation of the pressure distribution on the suction and pressure surfaces and the increase of both the lift and pressure drag.The position of the front stagnation point of the airfoil with a Mini-TED shifts downstream slightly compared with that of the NACA23012 prototype airfoil, which consequently leads to the increase of the flow velocity on the suction surface and the sup-pression of the flow separation near the trailing edge.
