Applied Computational Fluid Dynamics Techniques - Wiley Episode 2 Part 6 pps

... Flux-correctedtransportschemes 19 9 11 INCOMPRESSIBLE FLOW SOLVERS 2 01 11. 1Theadvectionoperator 2 01 11. 1 .1 Integrationalongcharacteristics 202 11 .1. 2 Taylor–Galerkin 202 11 .1. 3 Edge-basedupwinding 203 11 .2Thedivergenceoperator ... 211 11 .8Projectivepredictionofpressureincrements 212 11 .9Examples 213 11 .9 .1 vonKarmanvortexstreet 213 11 .9.2 NACA0 012 wing . 216 11 ....

Ngày tải lên: 06/08/2014, 01:21

... derive. 1 2 3 4 lpoed (1, 1) =1 lpoed (2 ,1) =2 lpoed (1, 2) =2 lpoed (2, 2)=3 lpoed (1, 3)=3 lpoed (2, 3) =1 lpoed (1, 4) =1 lpoed (2, 4)=4 lpoed (1, 5) =2 lpoed (2, 5)=4 lpoed (1, 6)=3 lpoed (2, 6)=4 1 2 3 4 5 6 Figure 2. 7. ... z min )/nsubz, DATA STRUCTURES AND ALGORITHMS 27 1 1 3 4 2 2 3 1 4 Root x y x 1 Root x y 2 1 1 2 2 31 1 32 1 3 54 2 2 3 1...

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... (4.2b) Applied Computational Fluid Dynamics Techniques: An Introduction Based on Finite Element Methods, Second Edition. Rainald Lửhner â 2008 John Wiley & Sons, Ltd. ISBN: 97 8-0 -4 7 0 -5 19 0 7-3 ... y 0 log c , (3 .54 ) and the total thickness of the semi-structured grid region is δ = c n +1 − 1 c − 1 y 0 . (3 .55 ) Typical values for c are 1. 10 <c< ;...

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... n t DNS 10 6 10 6. 4 10 3.2 10 8.4 10 4.2 10 13 .6 10 6. 8 10 7 10 6. 8 10 3.4 10 8.8 10 4.4 10 15 .2 10 7 .6 10 8 10 7.2 10 3 .6 10 9.2 10 4 .6 10 16 .8 10 8.4 10 9 10 7 .6 10 3.8 10 9 .6 10 4.8 10 18 .4 10 9.2 implying ... h 2 −h 2 −h 2 −h 2 2h 2   ·   ˆu 1 ˆu 5 ˆu 4   = 1 2   10 1 01 1 1 12   ·   ˆu 1 ˆu...

Ngày tải lên: 06/08/2014, 01:21

... notation of Figure 13 .19 , we can write x p = x 0 + i i g i , (13 .20 ) where g 1 ,2 = x 1 ,2 x 0 , g 3 = g 1 ì g 2 |g 1 ì g 2 | , (13 . 21 a,b) 1 ,2 = N 1 ,2 , 0 = 1 −α 1 − α 2 . (13 . 21 c,d) Point x p may ... (or L2 projection)  N i 2 N j 2 d ˆu j2 =  N i 2 N j 1 d ˆu j1 . (13 . 12 ) This may be expressed in matrix form as M c u 2 = r = Lu 1...

Ngày tải lên: 06/08/2014, 02:20

... ADAPTIVE MESH REFINEMENT 27 9 1 12 Level 0 1 N 2 N 1 12 1 N 2 N 1 12 Level 1 1 N 2 N 1 12 1 N 2 N 33 3 N 3 N 1 12 1 N 2 N 1 12 1 N 2 N 3 3 N (c)(b)(a) (a) (b) (c) Figure 14 .2. Mesh enrichment (a) ... INTERPOLATION 26 7 Table 13 .2. Particle-mesh interpolation timings ON=F,OFF=V ON=F Particle-tracing time (s) 25 7.0 17.6 MFLOP-rate recorded 1.11 20 . 82 Total runn...

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... 2. 92 2 .36 IBM-6000/ 530 1000 2- ChainTetra 2. 63 2. 62 IBM-6000/ 530 10 000 Edge 13. 4 1.00 IBM-6000/ 530 10 000 Triangle 7 .21 1.85 IBM-6000/ 530 10 000 Tetrahedron 5 .26 2. 54 IBM-6000/ 530 10 000 2- ChainTetra ... ipoi0-related arrays. However, such a specialized EFFICIENT USE OF COMPUTER HARDWARE 30 7 121 32 4 524 635 871089101111 1 nedge 121 32 4 524 635 871089101111 1 np...

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... Configuration: nedge =4, 179,771 mvecl % reduced i/a nvecl % reduced i/a nvecl 64 97 .22 63 97 .22 63 128 93.80 127 98.36 121 25 6 89 .43 25 5 97.87 22 3 5 12 86.15 510 97 . 24 3 84 1 0 24 82. 87 1018 96.77 608 20 48 79.30 20 26 ... 24 8 79 24 8 7– 12 23 776 23 776 13–18 7136 7136 19 24 0 21 44 25 –30 1 0 24 1 0 24 31–36 0 1 0 24 37– 42 0 336 Table 15.17. Inlet problem on...

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... 360 APPLIED COMPUTATIONAL FLUID DYNAMICS TECHNIQUES Mach-nr. (1. 025 , 3. 025 , 0.05) (a) (c) Mach-nr. (1. 025 , 3. 025 , 0.05) ( b ) Figure 16. 6. Macro-blocking: (a) one layer ... 1.00 Seque 518 1.17 10 30 22 7 2. 69 20 30 21 8 2. 80 Block 1 26 0 2. 35 420 00 elements respectively. The residual curves for the three different cases are compared in Figure 16. 8(e). As one c...

Ngày tải lên: 06/08/2014, 02:20

... Aftosmis et al. (20 00), LeVeque and Calhoon (20 01), Dadone and Grossman (20 02) , Baum et al. (20 03), - Euler with boundary layer corrections: Aftosmis et al. (20 06) , - low-Reynolds-number laminar ... layers; Applied Computational Fluid Dynamics Techniques: An Introduction Based on Finite Element Methods, Second Edition. Rainald Lửhner â 20 08 John Wiley & Sons,...

Ngày tải lên: 06/08/2014, 02:20

... APPLIED COMPUTATIONAL FLUID DYNAMICS TECHNIQUES pressure 7. 000e-01 4. 375 e-01 1 .75 0e-01 -8 .75 0e-01 -3 .500e-01 pressure 7. 000e-01 4. 375 e-01 1 .75 0e-01 -8 .75 0e-01 -3 .500e-01 abs(vel) 1.100e+00 8 .25 0e-01 5.500e-01 2. 75 0e-01 0.000e+00 abs(vel) 1.100e+00 8 .25 0e-01 5.500e-01 2. 75 0e-01 0.000e+00 (e) -0 .2 ... 4 07 pressure 7. 000e-01 4. 375 e-0...

Ngày tải lên: 06/08/2014, 02:20

... APPLIED COMPUTATIONAL FLUID DYNAMICS TECHNIQUES -4 0 -2 0 0 20 40 60 80 100 120 0 20 40 60 80 100 120 140 160 180 20 0 22 0 Position Time x_c -5 0 5 10 15 20 25 30 35 -4 0 -2 0 0 20 40 60 80 100 120 z-Position x-Position x_c ... wave elevation at the hull 426 APPLIED COMPUTATIONAL FLUID DYNAMICS TECHNIQUES (e) (f) -0 .1 -0 . 08 -0...

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... Kroo ( 199 3),Crispin ( 199 4),Quagliarella and Cioppa ( 199 4), Quagliarella ( 199 5), Doorly ( 199 5), Periaux ( 199 5), Yamamoto and Inoue ( 199 5), Vicini and Quagliarella ( 199 7, 199 9), Obayashi ( 199 8), Obayashi ... ( 198 5), Jameson ( 198 8, 199 5), Kuruvila et al. ( 199 5), Reuther and Jameson ( 199 5), Reuther et al. ( 199 6), Anderson and Venkata- krishnan ( 199 7), Elliott and P...

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... Roundtable (1998). 478 APPLIED COMPUTATIONAL FLUID DYNAMICS TECHNIQUES -0 .07 -0 .06 -0 .05 -0 .04 -0 .03 -0 . 02 -0 .01 0 -0 .08 -0 .06 -0 .04 -0 . 02 0 0. 02 0.04 0.06 0.08 (a) (b) Figure 20 .13. Wigley hull: ... France, May 23 28 (20 04). Huyse, L. and R.M. Lewis. Aerodynamic Shape Optimization of Two-Dimensional Airfoils Under Uncertain Co...

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... Problems; AIAA-0 2- 0451 (20 02) . Soto, O., R. Löhner and J.R. Cebral. An Implicit Monolithic Time Accurate Finite Element Scheme for Incompressible Flow Problems; AIAA-0 1 -2 626 -CP (20 01). Soto, ... for CFD; AIAA-0 2- 0 8 62 (20 02) . Tilch, R., A. Tabbal, M. Zhu, F. Dekker and R. Löhner. Combination of Body-Fitted and Embedded Grids for External Vehicle Aerodynamics; AIAA-0 7-1...

Ngày tải lên: 06/08/2014, 02:20