离散式粗糙元诱导翼型边界层转捩的数值和实验研究
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摘要
在Ma=0.6来流条件下,针对三维离散式圆柱粗糙元诱导NACA0012翼型边界层转捩问题开展了直接数值模拟(Direct numerical simulation,DNS)和油膜干涉风洞实验研究,分析了粗糙元诱导转捩的机理及粗糙元高度和相邻粗糙元间距对转捩位置的影响。结果表明,翼型表面粗糙元能够通过诱导出三维Λ涡和马蹄涡促进边界层转捩,达到转捩控制的效果。粗糙元高度和相邻粗糙元间距对边界层转捩有影响,且增加粗糙元高度和减小相邻粗糙元间距能够促进转捩。粗糙元高度对转捩的影响大于粗糙元间距,且对粗糙元后方区域影响大,对相邻粗糙元中间区域影响小。
The investigation of discrete roughness elements induced boundary layer transition on NACA0012 airfoil has been studied by direct numerical simulation(DNS)and oil-film interferometry technique,mainly focusing on the effect of roughness elements height and spacing on the boundary layer transition as well as the mechanism.The results show that,roughness elements on the airfoil surface can accelerate transition process by exciting three dimensionalΛvortices and horseshoe vortices.Increasing roughness element height and reducing spacing will advance the boundary layer transition.The influence is more intense on the area behind the roughness elements compared with that on the region between adjacent roughness elements.
The investigation of discrete roughness elements induced boundary layer transition on NACA0012 airfoil has been studied by direct numerical simulation(DNS)and oil-film interferometry technique,mainly focusing on the effect of roughness elements height and spacing on the boundary layer transition as well as the mechanism.The results show that,roughness elements on the airfoil surface can accelerate transition process by exciting three dimensionalΛvortices and horseshoe vortices.Increasing roughness element height and reducing spacing will advance the boundary layer transition.The influence is more intense on the area behind the roughness elements compared with that on the region between adjacent roughness elements.
引文
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[25]REDFORD J A,SANDHAM N D,ROBERTS G T.Compressibility effects on boundary-layer transition induced by an isolated roughness element[J].AIAA Journal,2010,48(12):2818-2830.
[2] KLEBANOFF P.Characteristics of turbulence in a boundary layer with zero pressure gradient:NACATR-1247[R].USA:[s.n.],1955.
[3] PRESTON J H.The minimum Reynolds number for a turbulent boundary layer and the selection of a transition device[J].Journal of Fluid Mechanics,1958,3(4):373-384.
[4]赵子杰,高超,张正科.新型人工转捩技术及风洞试验验证[J].航空学报,2015,36(6):1830-1838.ZHAO Zijie,GAO Chao,ZHANG Zhengke.An innovation artificial transition technique and its validation through wind tunnel test[J].Acta Aeronautica et Astronautica Sinica,2015,36(6):1830-1838.
[5] BRASLOW A L.Effect of distributed granular-type roughness on boundary-layer transition at supersonic speeds with and without surface cooling:NACA-RML58A17[R]:USA:[s.n.],1958.
[6] BRASLOW A L,KNOX E C.Simplified method for determination of critical height of distributed roughness particles for boundary-layer transition at Mach numbers from 0to 5 NACA-TN-4363[R].USA:[s.n.],1958.
[7]黄勇,钱丰学,于昆龙,等.基于柱状粗糙元的边界层人工转捩试验研究[J].实验流体力学,2006,20(3):59-62.HUANG Yong,QIAN Fengxue,YU Kunlong,et al.Experimental investigation on boundary-layer artificial transition based on transition trip disk[J].Journal of Experiments in Fluid Mechanics,2006,20(3):59-62.
[8] OWEN F K.Transition experiments on a flat plate at subsonic and supersonic speeds[J].AIAA Journal,1970,8(3):518-523.
[9] PINSON M, WANG T.Effects of leading-edge roughness on fluid flow and heat transfer in the transitional boundary layer over a flat plate[J].International Journal of Heat and Mass Transfer,1997,40(12):2813-2823.
[10] MOCHIZUKI M.Smoke observation on boundary layer transition caused by a spherical roughness element[J].Journal of the Physical Society of Japan,1961,16(5):995-1008.
[11]YE Q,SCHRIJER F F,SCARANO F.Geometry effect of isolated roughness on boundary layer transition investigated by tomographic PIV[J].International Journal of Heat and Fluid Flow,2016,61:31-44.
[12]王猛,袁洪杰,赵荣奂.离散粗糙元诱发边界层转捩的实验研究[J].空气动力学报,2016,34(1):47-52.WANG Meng,YUAN Hongjie,ZHAO Yonghuan.Experimental investigation on boundary layer transition induced by distributed roughness elements[J].Acta Aerodynamica Sinica,2016,34(1):47-52.
[13]DURANT A,ANDRE T,SCHNEIDER S P,et al.Mach 6quiet tunnel laminar to turbulent investigation of a generic hypersonic forebody:AIAA 2015-3575[R].USA:AIAA,2015.
[14]DANEHY P,BATHEL B,IVEY C,et al.NO PLIF study of hypersonic transition over a discrete hemispherical roughness element:AIAA 2009-0394[R].USA:AIAA,2009.
[15]RIZZETTA D P,VISBAL M R.Direct numerical simulations of flow past an array of distributed roughness elements[J].AIAA Journal,2007,45(8):1967-1976.
[16]PIOT E,CASALIS G,RIST U.Stability of the laminar boundary layer flow encountering a row of roughness elements:Biglobal stability approach and DNS[J].European Journal of Mechanics-B/Fluids,2008,27(6):684-706.
[17]CHOUDHARI M,LI F,CHANG C L,et al.Laminar-turbulent transition behind discrete roughness elements in a high-speed boundary layer:AIAA 2010-1575[R].USA:AIAA,2010.
[18]BERNARDINI M,PIROZZOLI S,ORLANDI P.Compressibility effects on roughness-induced boundary layer transition[J].International Journal of Heat and Fluid Flow,2012,35:45-51.
[19]CHEN L,TANG D B,LIU X B,et al.Evolution of the ring-like vortices and spike structure in transitional boundary layers[J].Science China,2010,53(3):514-520.
[20]DENG S,JIANG L,LIU C.DNS for flow separation control around an airfoil by pulsed jets[J].Computers&Fluids,2007,36(6):1040-1060.
[21]MAVRIPLIS D J,JAMESON A.Multigrid solution of the Navier-Stokes equations on triangular meshs[J].AIAA Journal,1990,28(8):1415-1425.
[22]DRIVER D M.Application of oil-film interferometry skin-friction measurement to large wind tunnels[J].Experiments in Fluids,2003,34(6):717-725.
[23] HUNT J C R,WARY A A,MOIN P.Eddies,stream,and convergence zones in turbulent flows:CTR-S88[R].USA:[s.n.],1988:193-208.
[24] MOCHIZUKI M.Smoke observation on boundary layer transition caused by a spherical roughness element[J].Journal of the Physical Society of Japan,1961,16(5):995-1008.
[25]REDFORD J A,SANDHAM N D,ROBERTS G T.Compressibility effects on boundary-layer transition induced by an isolated roughness element[J].AIAA Journal,2010,48(12):2818-2830.