Boundary-layer transition of advanced fighter wings at high-speed cruise conditions
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摘要
The achievement of laminar flow in the boundary layer at high-speed cruise conditions may further, in addition to shock-wave control, reduce the drag and extend the range of military fighter aircraft. To this end, a further investigation on transitional boundary-layer flow of fighter wings is needed due to different configurations from the wings used on conventional transport aircraft. In this paper, wind tunnel experiments and numerical simulations were conducted on three-dimensional transition of thin diamond-shaped wings used on advanced fighter aircraft at tran/supersonic design points. A newly proposed correlation of crossflow transition which includes the effect of surface roughness was introduced into the c-Rehttransition model. Predicted results were in good agreement with flow visualizations. Results showed that the strength of the crossflow component grew rapidly around the leading edge because of the severe flow acceleration, just as the same as wings with a large aspect ratio. However, there seemed no regular pattern of instabilitydominance variation in span-wise for a diamond configuration. The dominance of different instability mechanisms strongly depended on the local pressure distribution. Hereby, the research recommended a ‘‘roof-like" shape of pressure distribution to suppress both crossflow and Tollmien-Schlichting(T-S) instabilities. Besides, a sharp suction peak with a serious pressure rise should be cut off to avoid stronger instabilities. Further discussions also revealed an independence of the unit Reynolds number when transition was triggered by T-S instabilities. Aerodynamic force comparisons indicated that further benefit on drag reduction could be expected by including the three-dimensional transition effect into a wing design process.
The achievement of laminar flow in the boundary layer at high-speed cruise conditions may further, in addition to shock-wave control, reduce the drag and extend the range of military fighter aircraft. To this end, a further investigation on transitional boundary-layer flow of fighter wings is needed due to different configurations from the wings used on conventional transport aircraft. In this paper, wind tunnel experiments and numerical simulations were conducted on three-dimensional transition of thin diamond-shaped wings used on advanced fighter aircraft at tran/supersonic design points. A newly proposed correlation of crossflow transition which includes the effect of surface roughness was introduced into the c-Rehttransition model. Predicted results were in good agreement with flow visualizations. Results showed that the strength of the crossflow component grew rapidly around the leading edge because of the severe flow acceleration, just as the same as wings with a large aspect ratio. However, there seemed no regular pattern of instabilitydominance variation in span-wise for a diamond configuration. The dominance of different instability mechanisms strongly depended on the local pressure distribution. Hereby, the research recommended a ‘‘roof-like" shape of pressure distribution to suppress both crossflow and Tollmien-Schlichting(T-S) instabilities. Besides, a sharp suction peak with a serious pressure rise should be cut off to avoid stronger instabilities. Further discussions also revealed an independence of the unit Reynolds number when transition was triggered by T-S instabilities. Aerodynamic force comparisons indicated that further benefit on drag reduction could be expected by including the three-dimensional transition effect into a wing design process.
The achievement of laminar flow in the boundary layer at high-speed cruise conditions may further, in addition to shock-wave control, reduce the drag and extend the range of military fighter aircraft. To this end, a further investigation on transitional boundary-layer flow of fighter wings is needed due to different configurations from the wings used on conventional transport aircraft. In this paper, wind tunnel experiments and numerical simulations were conducted on three-dimensional transition of thin diamond-shaped wings used on advanced fighter aircraft at tran/supersonic design points. A newly proposed correlation of crossflow transition which includes the effect of surface roughness was introduced into the c-Rehttransition model. Predicted results were in good agreement with flow visualizations. Results showed that the strength of the crossflow component grew rapidly around the leading edge because of the severe flow acceleration, just as the same as wings with a large aspect ratio. However, there seemed no regular pattern of instabilitydominance variation in span-wise for a diamond configuration. The dominance of different instability mechanisms strongly depended on the local pressure distribution. Hereby, the research recommended a ‘‘roof-like" shape of pressure distribution to suppress both crossflow and Tollmien-Schlichting(T-S) instabilities. Besides, a sharp suction peak with a serious pressure rise should be cut off to avoid stronger instabilities. Further discussions also revealed an independence of the unit Reynolds number when transition was triggered by T-S instabilities. Aerodynamic force comparisons indicated that further benefit on drag reduction could be expected by including the three-dimensional transition effect into a wing design process.
引文
1.Sugiura H,Yoshida K,Tokugawa N,Takagi S,Nishizawa A.Transition measurements on the natural laminar flow wing at Mach 2.Journal of Aircraft 2002;39(6):996-1002.
2.Fey U,Engler RH,Egami Y,Iijima Y,Asai K,Jansen U,et al.Transition detection by temperature sensitive paint at cryogenic temperatures in the European Transonic Wind Tunnel(ETW).Proceedings of the 20th international congress on instrumentation in aerospace simulation facilities.2003.p.77-88
3.Halila GO,Bigarella EV,Azevedo JF.Numerical study on transitional flows using a correlation-based transition model.Journal of Aircraft 2016;53(4):922-41.
4.Wang C,Gao ZH.Refined aerodynamic design optimization of a wing with small aspect ratio.Sci Sin Tech 2015;45:643-53Chinese.
5.Jing ZR,Huang ZF.Instability analysis and drag coefficient prediction on a swept RAE2822 wing with constant lift coefficient.Chinese Journal of Aeronautics 2017;30(3):964-75.
6.Saric WS,Reed HL,White EB.Stability and transition of threedimensional boundary layers.Annual Review of Fluid Mechanics2003;35:413-440.
7.Arnal D,Casalis G.Laminar-turbulent transition prediction in three-dimensional flows.Progress in Aerospace Sciences 2000;36:173-91.
8.Dagenhart JR,Saric WS.Crossflow stability and transition experiments in swept-wing flow.Washington,D.C.:National Aeronautics and Space Administration;1999.Report No.:NASA/TP-1999-209344.
9.Yang Y,Zuo SH,Li XL,Li YL.Transition studies for the boundary layer on a swept wing based on sublimation technique.Journal of Experiments in Fluid Mechanics 2009;23(3):40-9Chinese.
10.Crouch JD,Ng LL.Variable N-factor method for transition prediction in three-dimensional boundary layers.AIAA Journal2000;38(2):211-6.
11.Radeztsky RH,Reibert MS,Saric WS.Effect of isolated micronsized roughness on transition in swept-wing flows.AIAA Journal1999;37(11):1370-7.
12.Wassermann P,Kloker M.Transition mechanisms in a threedimensional boundary-layer flow with pressure-gradient changeover.Journal of Fluid Mechanics 2005;530:265-93.
13.Langlois M,Masson C,Paraschivoiu I.Fully three-dimensional transition prediction on swept wings in transonic flows.Journal of Aircraft 1998;35(2):254-9.
14.Tokugawa N,Kwak DY,Yoshida K,Ueda Y.Transition measurement of natural laminar flow wing on supersonic experimental airplane NEXST-1.Journal of Aircraft 2008;45(5):1495-504.
15.Langlois M,Masson C,Kafyeke F,Paraschivoiu I.Automated method for transition prediction on wings in transonic flows.Journal of Aircraft 2002;39(3):460-8.
16.Muller C,Herbst F.Modelling of crossflow-induced transition based on local variables.Proceedings of the 6th European conference on computational fluid dynamics(ECFD VI).2014.
17.Hirschel EH,Cousteix J,Kordulla W.Three-dimensional attached viscous flow:basic principles and theoretical foundations.Berlin:Springer-Verlag;2014.p.30-2,216.
18.Chen MZ.Fundamentals of viscous fluid dynamics.1st ed.Beijing:High Education Press;2004.p.203-4 Chinese.
19.Schrauf G.Transition prediction using different linear stability analysis strategies.12th AIAA applied aerodynamics conference.Reston:AIAA;1994.
20.Schrauf G,Perraud J,Vitiello D,Lam F.A comparison of linear stability theories using f100 flight tests.15th AIAA applied aerodynamics conference.Reston:AIAA;1997.
21.Grabe C,Nie SY,Krumbein A.Transition transport modeling for the prediction of crossflow transition.34th AIAA applied aerodynamics conference.Reston:AIAA;2016.
22.Krumbein A,Krimmelbein N,Grabe C,Nie SY.Development and application of transition prediction techniques in an unstructured CFD code(invited).45th AIAA fluid dynamics conference.Reston:AIAA;2015.
23.Menter FR,Langtry RB,Likki SR,Suzen YB,Huang PG,Vo¨lker S.A correlation-based transition model using local variables Part1:model formulation.Journal of Turbomachinery 2004;128(3):413-22.
24.Menter FR,Langtry RB,Likki SR,Suzen YB,Huang PG,Vo¨lker S.A correlation-based transition model using local variables Part2:test cases and industrial applications.Journal of Turbomachinery2004;128(3):423-34.
25.Langtry RB.A correlation-based transition model using local variables for unstructured parallelized CFD codes dissertation.Stuttgart:University of Stuttgart;2006.
26.Langtry RB,Menter FR.Correlation-based transition modeling for unstructured parallelized computational fluid dynamics codes.AIAA Journal 2009;47(12):2894-906.
27.Krist SL,Biedron RT,Rumsey CL.CFL3D user’s manual(Ver.5.0).2nd ed.Washington,D.C.:NASA Langley Research Center;1998.Report No.:NASA/TM-1998-208444.
28.Langtry RB,Sengupta K,Yeh DT,Dorgan AJ.Extending the cRehtlocal correlation based transition model for crossflow effects.45th AIAA fluid dynamics conference.Reston:AIAA;2015.
29.Kreplin HP,Vollmers H,Meier HU.Wall shear stress measurements on an inclined prolate spheroid in the DFVLR 3m?3m low speed wind tunnel.Go¨ttingen Data Report;1985.Report No.:DFVLR IB 222-84/A33.
30.Savill AM.Some recent progress in the turbulence modeling of bypass transition.In:Near-wall turbulent flows.New York:Elsevier;1993.p.829.
31.Savill AM.One-point closures applied to transition.In:Turbulence and transition modeling.Netherlands:Dordrecht;1996.p.233-68.
32.Schubauer GB,Klebanoff PS.Contribution on the mechanics of boundary layer transition.Washington,D.C.:National Advisory Committee for Aeronautics;1955.Report No.:NACA/TN 3489.
33.Krimmelbein N,Radespiel R.Transition prediction for threedimensional flows using parallel computation.Computers and Fluids 2009;38:121-36.
34.Li RZ,Deng KW,Zhang YF,Chen HX.Pressure distribution guided supercritical wing optimization.Chinese Journal of Aeronautics 2018;31(9):1842-54.
2.Fey U,Engler RH,Egami Y,Iijima Y,Asai K,Jansen U,et al.Transition detection by temperature sensitive paint at cryogenic temperatures in the European Transonic Wind Tunnel(ETW).Proceedings of the 20th international congress on instrumentation in aerospace simulation facilities.2003.p.77-88
3.Halila GO,Bigarella EV,Azevedo JF.Numerical study on transitional flows using a correlation-based transition model.Journal of Aircraft 2016;53(4):922-41.
4.Wang C,Gao ZH.Refined aerodynamic design optimization of a wing with small aspect ratio.Sci Sin Tech 2015;45:643-53Chinese.
5.Jing ZR,Huang ZF.Instability analysis and drag coefficient prediction on a swept RAE2822 wing with constant lift coefficient.Chinese Journal of Aeronautics 2017;30(3):964-75.
6.Saric WS,Reed HL,White EB.Stability and transition of threedimensional boundary layers.Annual Review of Fluid Mechanics2003;35:413-440.
7.Arnal D,Casalis G.Laminar-turbulent transition prediction in three-dimensional flows.Progress in Aerospace Sciences 2000;36:173-91.
8.Dagenhart JR,Saric WS.Crossflow stability and transition experiments in swept-wing flow.Washington,D.C.:National Aeronautics and Space Administration;1999.Report No.:NASA/TP-1999-209344.
9.Yang Y,Zuo SH,Li XL,Li YL.Transition studies for the boundary layer on a swept wing based on sublimation technique.Journal of Experiments in Fluid Mechanics 2009;23(3):40-9Chinese.
10.Crouch JD,Ng LL.Variable N-factor method for transition prediction in three-dimensional boundary layers.AIAA Journal2000;38(2):211-6.
11.Radeztsky RH,Reibert MS,Saric WS.Effect of isolated micronsized roughness on transition in swept-wing flows.AIAA Journal1999;37(11):1370-7.
12.Wassermann P,Kloker M.Transition mechanisms in a threedimensional boundary-layer flow with pressure-gradient changeover.Journal of Fluid Mechanics 2005;530:265-93.
13.Langlois M,Masson C,Paraschivoiu I.Fully three-dimensional transition prediction on swept wings in transonic flows.Journal of Aircraft 1998;35(2):254-9.
14.Tokugawa N,Kwak DY,Yoshida K,Ueda Y.Transition measurement of natural laminar flow wing on supersonic experimental airplane NEXST-1.Journal of Aircraft 2008;45(5):1495-504.
15.Langlois M,Masson C,Kafyeke F,Paraschivoiu I.Automated method for transition prediction on wings in transonic flows.Journal of Aircraft 2002;39(3):460-8.
16.Muller C,Herbst F.Modelling of crossflow-induced transition based on local variables.Proceedings of the 6th European conference on computational fluid dynamics(ECFD VI).2014.
17.Hirschel EH,Cousteix J,Kordulla W.Three-dimensional attached viscous flow:basic principles and theoretical foundations.Berlin:Springer-Verlag;2014.p.30-2,216.
18.Chen MZ.Fundamentals of viscous fluid dynamics.1st ed.Beijing:High Education Press;2004.p.203-4 Chinese.
19.Schrauf G.Transition prediction using different linear stability analysis strategies.12th AIAA applied aerodynamics conference.Reston:AIAA;1994.
20.Schrauf G,Perraud J,Vitiello D,Lam F.A comparison of linear stability theories using f100 flight tests.15th AIAA applied aerodynamics conference.Reston:AIAA;1997.
21.Grabe C,Nie SY,Krumbein A.Transition transport modeling for the prediction of crossflow transition.34th AIAA applied aerodynamics conference.Reston:AIAA;2016.
22.Krumbein A,Krimmelbein N,Grabe C,Nie SY.Development and application of transition prediction techniques in an unstructured CFD code(invited).45th AIAA fluid dynamics conference.Reston:AIAA;2015.
23.Menter FR,Langtry RB,Likki SR,Suzen YB,Huang PG,Vo¨lker S.A correlation-based transition model using local variables Part1:model formulation.Journal of Turbomachinery 2004;128(3):413-22.
24.Menter FR,Langtry RB,Likki SR,Suzen YB,Huang PG,Vo¨lker S.A correlation-based transition model using local variables Part2:test cases and industrial applications.Journal of Turbomachinery2004;128(3):423-34.
25.Langtry RB.A correlation-based transition model using local variables for unstructured parallelized CFD codes dissertation.Stuttgart:University of Stuttgart;2006.
26.Langtry RB,Menter FR.Correlation-based transition modeling for unstructured parallelized computational fluid dynamics codes.AIAA Journal 2009;47(12):2894-906.
27.Krist SL,Biedron RT,Rumsey CL.CFL3D user’s manual(Ver.5.0).2nd ed.Washington,D.C.:NASA Langley Research Center;1998.Report No.:NASA/TM-1998-208444.
28.Langtry RB,Sengupta K,Yeh DT,Dorgan AJ.Extending the cRehtlocal correlation based transition model for crossflow effects.45th AIAA fluid dynamics conference.Reston:AIAA;2015.
29.Kreplin HP,Vollmers H,Meier HU.Wall shear stress measurements on an inclined prolate spheroid in the DFVLR 3m?3m low speed wind tunnel.Go¨ttingen Data Report;1985.Report No.:DFVLR IB 222-84/A33.
30.Savill AM.Some recent progress in the turbulence modeling of bypass transition.In:Near-wall turbulent flows.New York:Elsevier;1993.p.829.
31.Savill AM.One-point closures applied to transition.In:Turbulence and transition modeling.Netherlands:Dordrecht;1996.p.233-68.
32.Schubauer GB,Klebanoff PS.Contribution on the mechanics of boundary layer transition.Washington,D.C.:National Advisory Committee for Aeronautics;1955.Report No.:NACA/TN 3489.
33.Krimmelbein N,Radespiel R.Transition prediction for threedimensional flows using parallel computation.Computers and Fluids 2009;38:121-36.
34.Li RZ,Deng KW,Zhang YF,Chen HX.Pressure distribution guided supercritical wing optimization.Chinese Journal of Aeronautics 2018;31(9):1842-54.