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1 CFD JAXA CFD CFD Navier-Stokes
2 CFD CFD Navier-Stokes ,500,000 CFD Copyright Boeing CFD Boeing B777 HP
3 CFD European Transonic Wind tunnel (-163 ) JAXA 2mx2m CFD (Computational Fluid Dynamics) CFD CFD E. N. Tinoco AIAA
4 : *= , 0.8, 0.15 C 1/300,000C < L < 50C M =0.75, Re=6.5x % C 2% C Re = )()() ( ) = ( ) () Navier-Stokes Stokes Navier-Stokes 5 ρ ρu Q = ρv, ρw E ρu 2 ρu + p τ xx F = ρvu τ xy, ρwu τ zx T ρhu ( τ u) x k x Q F G H = 0 t x y z ρv ρuv τ xy 2 ρv + p τ yy G =, ρwv τ yz T ρhv ( τ u) y k y ρw ρuw τ xz H = ρvw τ yz 2 ρw + p τ zz T ρhw ( τ u) z k z
5 Reynolds Navier-Stokes(RANS) Euler Euler Prandtl-Glauret TRANAIR(1989) Boeing 90CFD TRANAIR F. T. Johnson et. al AIAA
6 CFD CFD CFD CFD - E. N. Tinoco AIAA F. T. Johnson et. al AIAA CFD CFD CFD Navier-Stokes
7 CFD CFD Navier-Stokes Navier-Stokes Stokes CFD ONERA M5 3 2 VP2600, VP CFD Capability Computing ONERA M
8 ( ) ONERA M SGI Onix CPU ONERA M5 NSIII NSIII AIAA Drag Prediction Workshop II (2003) DLR-F6 1% 0.5% Fujitsu PRIMEPOWER CPU % 5% 1 DLR-F
9 AIAA Drag Prediction Workshop 3 (2006) JAXA
10 0.5% 1 Capability Computing C CD D CFD CFD Navier-Stokes UPACS WB UPACS FX2B TAS WB TAS FX2B E E E E E E E-05 N ^(-2/3) 1/N^(2/3)
11 CFD CFD CFD 3 RANS RANS 5000 B747 Airbus A CFD,,
12 CFD CFD European EUROLIFT 233 AIAA NASA Langley CFD Web JAXA CFD 100 Trapezoidal wing models JAXA CFD Code : TAS (Tohoku Univ. Aerodynamic Simulation Code) 6 Spalart-Allmaras 60m/s Re=2.1x10 6 FTFHLD JAXA NSIII (PRIMEPOWER HPC2500) Upper Surface Unstructured hybrid mesh Lower Surface -23- JAXA wind tunnel model B.L. transition locations (AoA=10deg)
13 (C L -α) CFD C L 2 Exp. (Corrected) Comp. (Fully Turb.) Angle of attack Exp. α=10.55 Comp.(w/oFTF) α=10 Exp. α=15.54 Comp.(w/oFTF) α=
14 CFD CFD Navier-Stokes 10, E. N. Tinoco AIAA
15 vs Kriging ANOVA (analysis of variance) SOM (self-organizing map)
16 CFD AIAA Applied Aerodynamics Conf MSC. NASTRAN / Navier-Stokes solver TAS) Block Fuel Aerodynamic Model (Unstructured mesh) Adaptive Range Multi-Objective Genetic Algorithm Structural Model (Wing box: Shell elements) Modified PARSEC : 9 design variables * 3 cross sections : 6 spanwise locations : 2 positions at kink and tip
17 1 1 ARMOGA Individual # 1 Individual # 8 Static Aeroelastic Analysis Module Euler =Const. No Subsonic Static Analysis Displacement Converge? Yes 3conditions Euler eq. N-S eq CFD Aerodynamic Model ite=ite+1 ite=1 Transonic Euler =Const. No Static Analysis Displacement Converge? Yes 5conditions Structural Model if (ite=1) then Strength/Flutter Optimization endif Euler =Const. Static Analysis Displacement Converge? Yes 3conditions N-S S Comps. - Evaluation of Three Objective Functions Block Fuel Max Takeoff Weight C D divergence (MDD) -Check of Constraints MLD Fuel Quantity Block Fuel Module Individual # i Off-design No : Nondominated solution 4counts initial solution C D divergence Block Fuel [kg] 10kg 50kg Max Takeoff Weight [kg]
18 SOM Block Fuel Max Takeoff Weight C D Divergence N-S N-S1 N-S 100 CFD
19 /NEDO Navier-Stokes CFD 10 RANSCFD CFD 100 RANS Large Eddy Simulation
Contents
Simulation Engineering Solution s NS Plant Designing Corporation Contents 2014 1 2 2014 2014 3 4 2014 - i u j 2014 5 N= 0.3N =200 mm N=1581.9N 6 2014 Z Y X 2014 7 by Marc) 8 2014 CFDEM LIGGGHTS DEM CFD
工学的な設計のための流れと熱の数値シミュレーション
247 Introduction of Computational Simulation Methods of Flow and Heat Transfer for Engineering Design Minoru SHIRAZAKI Masako IWATA Ryutaro HIMENO PC CAD CAD 248 Voxel CAD Navier-Stokes v 1 + ( v ) v =
(5) 75 (a) (b) ( 1 ) v ( 1 ) E E 1 v (a) ( 1 ) x E E (b) (a) (b)
(5) 74 Re, bondar laer (Prandtl) Re z ω z = x (5) 75 (a) (b) ( 1 ) v ( 1 ) E E 1 v (a) ( 1 ) x E E (b) (a) (b) (5) 76 l V x ) 1/ 1 ( 1 1 1 δ δ = x Re x p V x t V l l (1-1) 1/ 1 δ δ δ δ = x Re p V x t V
II ( ) (7/31) II ( [ (3.4)] Navier Stokes [ (6/29)] Navier Stokes 3 [ (6/19)] Re
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II 29 7 29-7-27 ( ) (7/31) II (http://www.damp.tottori-u.ac.jp/~ooshida/edu/fluid/) [ (3.4)] Navier Stokes [ (6/29)] Navier Stokes 3 [ (6/19)] Reynolds [ (4.6), (45.8)] [ p.186] Navier Stokes I Euler Navier
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II 14 14-7-8 8/4 II (http://www.damp.tottori-u.ac.jp/~ooshida/edu/fluid/) [ (3.4)] Navier Stokes [ 6/ ] Navier Stokes 3 [ ] Reynolds [ (4.6), (45.8)] [ p.186] Navier Stokes I 1 balance law t (ρv i )+ j
A03-2.dvi
14 A3-2 Numerical Analyses in the Secondary Combustion Chamber of the Ducted Rocket Engine 184-8588 2-24-16 E-mail: kikumoto@starcadmechtuatacjp Kousuke KIKUMOTO Dept of Mech Systems Eng Tokyo Noko Univ
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15 C11-4 Numerical analysis of flame propagation in a combustor of an aircraft gas turbine, 4-6-1 E-mail: tominaga@icebeer.iis.u-tokyo.ac.jp, 2-11-16 E-mail: ntani@iis.u-tokyo.ac.jp, 4-6-1 E-mail: itoh@icebeer.iis.u-tokyo.ac.jp,
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41 COSMOS-V, an Aerodynamic Noise Simulator Nariaki Horinouchi COSMOS-V COSMOS-V COSMOS-V 3 The present and future computational problems of the aerodynamic noise analysis using COSMOS-V, our in-house
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オープン CAE 関東 数値流体力学 輪講 第 4 回 第 3 章 : 乱流とそのモデリング (3) [3.5~3.7.1 p.64~75] 日時 :2013 年 11 月 10 日 14:00~ 場所 : 日本 新宿 2013/11/10 数値流体力学 輪講第 4 回 1
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オープン CAE 勉強会 @ 関東 数値流体力学 輪講 第 4 回 第 3 章 : 乱流とそのモデリング (3 [3.5~3.7.1 p.64~75] 日時 :2013 年 11 月 10 日 14:00~ 場所 : 日本 ESI@ 新宿 1 数値流体力学 輪講に関して 目的 数値流体力学の知識 ( 特に理論ベース を深め OpenFOAM の利用に役立てること 本輪講で学ぶもの 数値流体力学の理論や計算手法の概要
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Title 混合体モデルに基づく圧縮性流体と移動する固体の熱連成計算手法 Author(s) 鳥生, 大祐 ; 牛島, 省 Citation 土木学会論文集 A2( 応用力学 ) = Journal of Japan Civil Engineers, Ser. A2 (2017), 73 Issue
Title 混合体モデルに基づく圧縮性流体と移動する固体の熱連成計算手法 Author(s) 鳥生, 大祐 ; 牛島, 省 Citation 土木学会論文集 A2( 応用力学 ) = Journal of Japan Civil Engineers, Ser. A2 (2017), 73 Issue Date 2017 URL http://hdl.handle.net/2433/229150 Right
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5212017 19 1 * 1 1 1, 2 1 Development of a Numerical Model for Predicting the Atmospheric Dispersion of Hydrogen-Sulfide Emitted from Geothermal Power Plants Hiroki Ono 1 *, Hiroshi Takimoto 1, Ayumu Sato
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