第 40 回流体力学講演会 / 航空宇宙数値シミュレ ション技術シンポジウム 2008 論文集 -Re Validation of -Re Transition Model and Modeling of Crossflow Instability Yuto Watanabe, Takashi Mi

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1 第 0 回流体力学講演会 / 航空宇宙数値シミュレ ション技術シンポジウム 008 論文集 -Re Validaion of -Re Transiion Model and Modeling of Crossflow Insabiliy Yuo Waanabe, Taashi Misaa, Shigeru Obayashi, Tauma Kao, Yuichiro Saii, Toshiyui Arima and Yoshihiro Yamaguchi ABSTRACT The Re ransiion model was applied o predic he boundary layer ransiion on NACA0015 airfoil and validaed by comparing he simulaion resuls wih experimen. The comparison showed he lac of predicion accuracy in negaive pressure gradien. The crossow parameer proposed by Kohama e al. was seleced as a candidae for crossflow modeling and is implemenaion was aemped only using local flow variables. The crossflow parameer was evaluaed on he flowfield of S5010 swep wing and compared wih oher crossflow parameers. The resuls showed he poenial effeciveness of his crierion. LES (Large Eddy Simulaion) DNS (Direc Numerical Simulaion) RANS (Reynolds Averaged Navier- Soes) 10 5 e N (1) () LESDNS (3,) Mener Re (5-7) Navier-Soes Tohou universiy Aerodynamic Simulaion code (TAS code) (8-10) Re (11) JAXA- HLD (1) Re Re Re TAS code Weiss (13,1) U-MUSCL (15) LU- SGS (16) U ref minc, maxu, Ku (1) c u u K K=1.0 K=3.0 (1) U-MUSCL ~ L rˆ Q Q Q Q 1 Q () i1 i i1 i Q =0 1 = (15) =0.5 Re Mener Re (5-7) Re Re Re x, ~ y max.193re x (3) Re Re i

2 宇宙航空研究開発機構特別資料 JAXA-SP Tu Re Re Tu Re f ( Tu, ) () () Tu Re Re Re exp 7.08 Tu F (5) F F K, Tu 3 3.0, K e ( ) (6) 3, K K 0.18K 0.011K [1 e Tu 1.5 Tu e e ( ) (7) du 6 du K 10 (8) ds U ds (5) F(, K) Re Mener Tu Re (11,1) Re R e Re Re (3) Re (=(y )/ R e Re -SST R e R ~ e U R ~ e R ~ e (9) x x x P U x x x P E P E 1 1 (10) (9) P Tu R e (10) P 1 -E 1 P -E P 1 (9) (11)-(19)(10)(0)-(33) P c Re R ~ e 1 F (11) 500 (1) U y 1/ ce F min max Fwae e,1.0,1.0 (13) 1.0 1/ ce R ~ e BL (1) U 15 BL (15) BL ] y 50 BL U (16) y Re (17) F wae e Re 1e5 (18) c 0.03,.0 (19) c onse P 1 Flenghca 1S F (0) R ~ 1. l F e (1) lengh U Re E c () 1 e1p 1 y S Re (3) v F Re () onse 1.193Re c Rec 0.9R ~ e (5) F min max F, F,.0 (6) onse onse1 onse1 R T (7) 3 RT F max 1, 0 (8) onse3.5 Fonse maxfonse Fonse3,0 (9) P c a F urb (30) E c (31) ep RT F urb e (3) c.0, c.0, c 0.5, c 50, c 0.06, c 1.0 e1 1 a1 e a (33) F lengh Re c (11,1) Re -SST u x x x (3) ~ ~ P D ~ P eff P (35) ~ D min max,0.1,1. 0 D (36) eff eff max, (37) eff sep sep Re min max 1,0 Frea, F (38) 3.35 Rec R 0 T F e (39) rea

3 第 0 回流体力学講演会 / 航空宇宙数値シミュレ ション技術シンポジウム 008 論文集 C K (17) Ve C (0) r V e r V e r r NACA TAS code 1 55,000 y + 1 (18) Poenial flow sreamline Frene frame 1 Frene framee 1 V e = V e e 1 e 1 e 1 = V e / V e e 1 s Frene-Serre de1 ( s) e (1) ds e e 1 Poenial flow sreamline = e 1 n b b = n b b e b () r 1 1 r (3) b e b r Re 1 NACA0015 [m/s] Re [deg] , (0.0) , 0, 3, (0.05) (18) =0 =3 =5 5 5 (18) 5 6

4 宇宙航空研究開発機構特別資料 JAXA-SP (11) (11) =0[deg] =3[deg] 5 6 U = 30[m/s] = 3[deg] (11) Tu Re Re Mener 30deg U CF max Re CF C K CF max 0. 1 Re CF U () % U CF max C K Re CF C K

5 第 0 回流体力学講演会 / 航空宇宙数値シミュレ ション技術シンポジウム 008 論文集 Direcion 30deg 7 S5010 M =0.07Re= =0, -[deg]= U CF max Re CF C K =0 U CF max =0 - =0 Re CF C K =- (0) U CF max Re CF C K 11 U CF max U CF max Re CF C K (0) Re CF C K Re CF C K =0 C K Re CF C K C K ~.8 (17) (0) =- C K C K C K 8 U CF max, =0[deg] =-[deg] 9 Re CF, =0 =-[deg] 10 C, K =0 =-[deg] Direcion Direcion Direcion Uniform flow direcion

6 宇宙航空研究開発機構特別資料 JAXA-SP (c) (d) 11 =-[deg] U CF max (c) Re CF (d) C K C K Re C K C K C K C K 1) Soc, H. W., Infinie Swep-Wing Navier-Soes Compuaions wih e N Transiion Predicion, AIAA Journal, Vol. 3, No. 6, 005, pp ) Krumbein, A., Auomaic Transiion Predicion and Applicaion o 3D High-Lif Configuraions, AIAA paper , ) Aobe, T., Kuroai, T., Sumi, T. and Taagi, S., Challenge for Naural Transiion Simulaion of Wing Boundary Layer wih an Innovaive 3-D LES Technique, AIAA paper , 006. ),,,, 005, p. 3, ) Mener, F. R., Langry, R. B., Lii, S. R., Suzen, Y. B., Huang, P. G. and Völer, S., A Correlaion-Based Transiion Model Using Local Variables Par I Model Formulaion, Proceedings of ASME Turbo Expo 00, Vienna, Ausria, 00, pp ) Langry, R. B., Mener, F. R., Lii, S. R., Suzen, Y. B., Huang, P. G. and Völer, S., A Correlaion-Based Transiion Model Using Local Variables Par II - Tes Cases and Indusrial Applicaions, Proceedings of ASME Turbo Expo 00, Vienna, Ausria, 00, pp ) Sharov, D. and Naahashi, K., Reordering of Hybrid Unsrucured Grids for Lower-Upper Symmeric Gauss- Seidel Compuaions, AIAA Journal, Vol. 36, No. 3, 1998, pp ) Sharov, D. and Naahashi, K., Hybrid Prismaic/ Terahedral Grid Generaion for Viscous Flow Applicaions, AIAA paper , ) Io, Y. and Naahashi, K., Direc Surface Triangulaion Using Sereolihography(STL) Daa, AIAA paper , ) Io, Y. and Naahashi, K., Unsrucured Mesh Generaion for Viscous Flow Compuaions, Proceedings of he 11h Inernaional Meshing Roundable, Ihaca, NY, 00, pp ) Misaa, T., and Obayashi, S., Applicaion of Local Correlaion-Based Transiion Model o Flows around Wings, AIAA Paper , ) Toyoda, A., Misaa, T., and Obayashi, S., An Applicaion of Local Correlaion-Based Transiion Model o JAXA High-Lif Configuraion Model, 5 h AIAA Applied Aerodynamics Conference, 007, AIAA ) Weiss, J.M., Maruszewsi, J. P. and Smih, W. A., Precondiioned Applied o Variable and Consan Densiy Flows, AIAA Journal,Vol. 33,No. 11, 1995, pp This is a simple example of he paper forma for ANSS 008 1) Luos, H., Baum, J. D. and Löhner, R., Exension of Haren- Lax-van Leer Scheme for Flows a All Speeds, AIAA Journal, Vol. 3, No. 6, 005, pp ) Burg, C. O. E., Higher Order Variable Exrapolaion For Unsrucured Finie Volume RANS Flow Solvers, 17 h AIAA Compuaional Fluid Dynamics Conference, 005, AIAA ) Sharov, D. and Naahashi, K., Low Speed Precondiioning and LU-SGS Scheme for 3-D Viscous Flow Compuaion on Unsrucured Grids, AIAA paper , ) Kohama, Y., and Davis, S., A New Parameer for Predicing Crossflow Insabiliy, JSME inernaional Series B, Fluids and hermal engineering, Vol.36-B, No.1 ( ) pp , ),, Vol. 003pp ) SST 53 pp ) pp ),,,, NACA001, JAXA-RR , 006

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