Numerical and experimental investigation into hypersonic boundary layer transition induced by roughness elements
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摘要
In this work, the Direct Numerical Simulation(DNS) and Oil-Film Interferometry(OFI)technique are used to investigate the hypersonic boundary layer transition induced by single and double roughness elements at Mach number 5. For single roughness, the DNS results showed that both horseshoe vortices and hairpin vortices caused by shear layer instability can affect the boundary layer instability. The generation of the near-wall unstable structure is the key point of boundary layer transition behind the roughness element. At the downstream of the roughness element, the interaction between horseshoe vortices and hairpin vortices will spread in the spanwise direction.For double roughness elements, the effect of the spacing between roughness elements on the transition is studied. It is found that the case of higher spacing between roughness elements is more effective for inducing transition than the lower one. The interaction between two adjacent roughness elements can suppress the evolution of horseshoe vortices in the downstream and trigger the instability of shear layer. Thus, the transition will be suppressed accordingly.
In this work, the Direct Numerical Simulation(DNS) and Oil-Film Interferometry(OFI)technique are used to investigate the hypersonic boundary layer transition induced by single and double roughness elements at Mach number 5. For single roughness, the DNS results showed that both horseshoe vortices and hairpin vortices caused by shear layer instability can affect the boundary layer instability. The generation of the near-wall unstable structure is the key point of boundary layer transition behind the roughness element. At the downstream of the roughness element, the interaction between horseshoe vortices and hairpin vortices will spread in the spanwise direction.For double roughness elements, the effect of the spacing between roughness elements on the transition is studied. It is found that the case of higher spacing between roughness elements is more effective for inducing transition than the lower one. The interaction between two adjacent roughness elements can suppress the evolution of horseshoe vortices in the downstream and trigger the instability of shear layer. Thus, the transition will be suppressed accordingly.
In this work, the Direct Numerical Simulation(DNS) and Oil-Film Interferometry(OFI)technique are used to investigate the hypersonic boundary layer transition induced by single and double roughness elements at Mach number 5. For single roughness, the DNS results showed that both horseshoe vortices and hairpin vortices caused by shear layer instability can affect the boundary layer instability. The generation of the near-wall unstable structure is the key point of boundary layer transition behind the roughness element. At the downstream of the roughness element, the interaction between horseshoe vortices and hairpin vortices will spread in the spanwise direction.For double roughness elements, the effect of the spacing between roughness elements on the transition is studied. It is found that the case of higher spacing between roughness elements is more effective for inducing transition than the lower one. The interaction between two adjacent roughness elements can suppress the evolution of horseshoe vortices in the downstream and trigger the instability of shear layer. Thus, the transition will be suppressed accordingly.
引文
1.Schneider SP.Effects of roughness on hypersonic boundary-layer transition.J Spacecr Rockets 2008;45(2):193-209.
2.Schneider SP.Hypersonic laminar-turbulent transition on circular cones and scramjet forebodies.Prog Aeosp Sci 2004;40(1-2):1-50.
3.Van Driest ER.The effect of controlled three-dimensional roughness on boundary-layer transition at supersonic speeds.JAerosp Sci 1960;27(4):261-71.
4.Whitehead AH.Flow-field and drag characteristics of several boundary-layer tripping elements in hypersonic flow.Washington,D.C.:NASA;1969.Report No.:NASA-TN-D5454.
5.Berry SA,Auslender AH,Dilley AD,Calleja JF.Hypersonic boundary-layer trip development for Hyper-X.J Spacecr Rockets2001;38(6):853-64.
6.Tirtey S,Louis W,Olivier C.Characterization of hypersonic roughness induced transition for the EXPERT flight experiment.16th AIAA/DLR/DGLR international space planes and hypersonic systems and technologies conference.Reston:AIAA;2009.
7.Danehy PM,Bathel B,Ivey C,Inman JA,Jones SB.NO PLIFstudy of hypersonic transition over a discrete hemispherical roughness element.47th AIAA aerospace sciences meeting including the new horizons forum and aerospace exposition.Reston:AIAA;2009.
8.Wheaton BM,Schneider SP.Roughness-induced instability in a hypersonic laminar boundary layer.AIAA J 2012;50(6):1245-56.
9.Ye QQ,Schrijer F,Scarano F.Tomographic PIV measurement of hypersonic boundary layer transition past a micro-ramp.47th AIAA fluid dynamics conference.Reston:AIAA;2017.
10.Subbareddy PK,Bartkowicz MD,Candler GV.Direct numerical simulation of high-speed transition due to an isolated roughness element.J Fluid Mech 2014;748:848-78.
11.Duan ZW,Xiao ZX,Fu S.Direct numerical simulation of hypersonic transition induced by an isolated cylindrical roughness element.Sci China-Phys Mech Astron 2014;57(12):2330-45.
12.Duan ZW,Xiao ZX.Direct numerical simulation of geometrical parameter effects on the hypersonic ramp-induced transition.7th AIAA theoretical fluid mechanics conference.Reston:AIAA;2014.
13.Gao WZ,Li ZF,Yang JM,Zeng YS.Effects of trips on the oscillatory flow of an axisymmetric hypersonic inlet with downstream throttle.Chin J Aeronaut 2018;31(2):225-36.
14.Shu CW,Osher S.Efficient implementation of essentially nonoscillatory shock-capturing scheme.J Comput Phys1988;77:39-471.
15.Chen L,Tang DB,Liu XB,Oliveira M,Liu CQ.Evolution of the ring-like vortices and spike structure in transitional boundary layers.Sci China-Phys Mech Astron 2010;53(3):514-20.
16.Chen L,Tang DB,Liu CQ.Numerical studies on evolution of secondary streamwise vortices in transitional boundary layers.Appl Math Mech Engl Ed 2011;32(4):449-58.
17.Lele SK.Compact finite difference schemes with spectral-like resolution.J Comput Phys 1992;103:16-42.
18.Zhu ZB,Yuan XJ,Chen L.Zone decomposition parallel algorithm of high order compact scheme.Chin J Comput Mech2014;32(6):825-30[Chinese].
19.Driver DM.Application of oil-film interferometry skin-friction measurement to large wind tunnels.Exp Fluids 2003;34(6):717-25.
20.Driver DM,Zilliac GG.Oil-film interferometry shear stress measurements in large wind tunnels-technique and applications.24th AIAA aerodynamic measurement technology and ground testing conference.Reston:AIAA;2004.
21.Driver DM,Drake A.Skin friction measurements using oil-film interferometry in NASA’s 11-Foot Transonic Wind Tunnel.AIAAJ 2008;46(10):2401-7.
22.Bartkowicz MD.Numerical simulations of hypersonic boundary layer transition[dissertation].Minnesota:University of Minnesota;2012.
2.Schneider SP.Hypersonic laminar-turbulent transition on circular cones and scramjet forebodies.Prog Aeosp Sci 2004;40(1-2):1-50.
3.Van Driest ER.The effect of controlled three-dimensional roughness on boundary-layer transition at supersonic speeds.JAerosp Sci 1960;27(4):261-71.
4.Whitehead AH.Flow-field and drag characteristics of several boundary-layer tripping elements in hypersonic flow.Washington,D.C.:NASA;1969.Report No.:NASA-TN-D5454.
5.Berry SA,Auslender AH,Dilley AD,Calleja JF.Hypersonic boundary-layer trip development for Hyper-X.J Spacecr Rockets2001;38(6):853-64.
6.Tirtey S,Louis W,Olivier C.Characterization of hypersonic roughness induced transition for the EXPERT flight experiment.16th AIAA/DLR/DGLR international space planes and hypersonic systems and technologies conference.Reston:AIAA;2009.
7.Danehy PM,Bathel B,Ivey C,Inman JA,Jones SB.NO PLIFstudy of hypersonic transition over a discrete hemispherical roughness element.47th AIAA aerospace sciences meeting including the new horizons forum and aerospace exposition.Reston:AIAA;2009.
8.Wheaton BM,Schneider SP.Roughness-induced instability in a hypersonic laminar boundary layer.AIAA J 2012;50(6):1245-56.
9.Ye QQ,Schrijer F,Scarano F.Tomographic PIV measurement of hypersonic boundary layer transition past a micro-ramp.47th AIAA fluid dynamics conference.Reston:AIAA;2017.
10.Subbareddy PK,Bartkowicz MD,Candler GV.Direct numerical simulation of high-speed transition due to an isolated roughness element.J Fluid Mech 2014;748:848-78.
11.Duan ZW,Xiao ZX,Fu S.Direct numerical simulation of hypersonic transition induced by an isolated cylindrical roughness element.Sci China-Phys Mech Astron 2014;57(12):2330-45.
12.Duan ZW,Xiao ZX.Direct numerical simulation of geometrical parameter effects on the hypersonic ramp-induced transition.7th AIAA theoretical fluid mechanics conference.Reston:AIAA;2014.
13.Gao WZ,Li ZF,Yang JM,Zeng YS.Effects of trips on the oscillatory flow of an axisymmetric hypersonic inlet with downstream throttle.Chin J Aeronaut 2018;31(2):225-36.
14.Shu CW,Osher S.Efficient implementation of essentially nonoscillatory shock-capturing scheme.J Comput Phys1988;77:39-471.
15.Chen L,Tang DB,Liu XB,Oliveira M,Liu CQ.Evolution of the ring-like vortices and spike structure in transitional boundary layers.Sci China-Phys Mech Astron 2010;53(3):514-20.
16.Chen L,Tang DB,Liu CQ.Numerical studies on evolution of secondary streamwise vortices in transitional boundary layers.Appl Math Mech Engl Ed 2011;32(4):449-58.
17.Lele SK.Compact finite difference schemes with spectral-like resolution.J Comput Phys 1992;103:16-42.
18.Zhu ZB,Yuan XJ,Chen L.Zone decomposition parallel algorithm of high order compact scheme.Chin J Comput Mech2014;32(6):825-30[Chinese].
19.Driver DM.Application of oil-film interferometry skin-friction measurement to large wind tunnels.Exp Fluids 2003;34(6):717-25.
20.Driver DM,Zilliac GG.Oil-film interferometry shear stress measurements in large wind tunnels-technique and applications.24th AIAA aerodynamic measurement technology and ground testing conference.Reston:AIAA;2004.
21.Driver DM,Drake A.Skin friction measurements using oil-film interferometry in NASA’s 11-Foot Transonic Wind Tunnel.AIAAJ 2008;46(10):2401-7.
22.Bartkowicz MD.Numerical simulations of hypersonic boundary layer transition[dissertation].Minnesota:University of Minnesota;2012.
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