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1 第 46 回流体力学講演会 / 第 32 回航空宇宙数値シミュレーション技術シンポジウム論文集 151 JAXA, 鳥取大学 Construction of Interface model in Solid-fluid Interaction Problem and Application Construction of Interface model to High in Speed Solid-fluid Flow Interaction Analysis Problem and Application to High Speed Flow Analysis by Takuji Kurotaki (JAXA) and Takahiro by SumiTottori University Takuji Kurotaki (JAXA) and Takahiro SumiTottori University ABSTRACT A new interface model in solid-fluid interaction problem is presented. ABSTRACT A level set function is used for the definition of shapes and flow A properties new interface are corrected model in within solid-fluid three layers interaction of stencils problem around is presented. interface. This A level approach set function is very is simple used for and the robust definition and can of capture shapes the and detail flow of properties flow structures are corrected including within discontinuities three layers of such stencils as shock around waves interface. and slip This lines approach etc.. Some is very basic simple important and robust 2-D and Euler can flow capture problem the detail are solved of flow to structures verify effects including of this discontinuities approach with such WCNS as shock (Weighted waves Compact and slip Nonlinear lines etc.. Scheme) Some basic including important a new 2-D type Euler of compact flow problem scheme are to improve solved to robustness verify effects including of this the approach transonic with flow WCNS around (Weighted a 2-D airfoil, Compact the supersonic Nonlinear Scheme) duct flow including around a a prism new type and a of circular compact cylinder scheme and to the improve moving-shock/obstacle robustness including interaction the transonic problem flow (Schardin s around a 2-D problem). airfoil, the The supersonic etension duct of this flow method around to a prism the moving and a circular problem cylinder with body and deformation the moving-shock/obstacle is straightforward. interaction problem (Schardin s problem). The etension of this method to the moving problem with body deformation is straightforward. (1) DEM-DNS (1) IBM(Immersed boundary method) (2) WCNS (3)(4) N u uj j p E e (1) (Weighted Compact Nonlinear Scheme: WCNS ) (5), (6) q i (5)
2 152 宇宙航空研究開発機構特別資料 JAXA-SP-14-1 p smoothness indicator k (3) (7) 3 TVD (5) Fig. 1 = j j-1 ( i, j ) ( i, j-1 )( i, j-2 ) (a) ( i, j ) (b) ( i, j-1 ) ( i, j-1 ) ( i-1, j )( i, j )( i+1, j ) s1s2s3 j ( i, j ) s1s2 s2s3 j Fig. 1 (c) ( i, j-2 ) j-1 Fig.2 (()) () ( i, j ) Fig. 1 Schematic image around interface (Normal condition). Fig. 2 Schematic image around interface (Special condition) NACA12
3 第 46 回流体力学講演会 / 第 32 回航空宇宙数値シミュレーション技術シンポジウム論文集 153 ((8)) 6% 35% (=.2) (=.2) (y=.625) Roe scheme CFL=.6 Fig. 3 Fig. 4 y Fig. 3 Mach Contours (NACA12, M=.8, = 1.25deg.,=.2,y=.625). cc L=12 mmly=3 mm 2 11 mm 5 mm LLF (9) CFL=.5 Fig. 5 Fig (2) Fig D /D=.293 (2) Fig. 6 /D. 3 Ms=1.3 Schardin (2) Fig.7 (2) 3 b= 2mm 54mm L=2mmLy=15mm.5MP 3K t , Roe scheme CFL =.5 Fig.8 t=138sec shadowgraph (2)(2), Fig.14 t=28 178sec Fig. 9 cc y Fig. 4 Mach Contours (NACA12, M=.8, = 1.25deg.,=.1,y=.625). WCNS WCNS
4 154 宇宙航空研究開発機構特別資料 JAXA-SP Fig.5 Density Contours (prism, M=3.5) Fig.6 Density Contours (Circular cylinder, M=3.5) ཧ (1) 㓇 ᖿኵ ⴭ, య ࢩ ࢩ, ၿฟ, (212). (2) A. Chaudhuri, A. Hadjadj and A. Chinnayya, On the use of immersed boundary methods for shock/obstacle interactions, Journal of Computational Physics, 23, (211), pp (3) ఫ㸪㯮, "㔜 ࡁࢥ ࢡ ࢫ ሀ ᛶ ゎ ᗘ ヨ," 27 ᅇ ὶయຊᏛࢩ ࢪ, (213), C3-2. (4) 㯮, ఫ, " Anti-diffusion interface sharpening technique ᛂ ࡋࡓ㔜 ࢥ ࢡ ࢫ ࡅ Ẽయ 㐃 ᥋ゐ㠃 ゎ ᗘ ࡘ," 27 ᅇ ὶయ ຊᏛࢩ ࢪ, (213), C3-3. (5) G. S. Jiang, C. W. Shu, Efficient implementation of weighted ENO scheme, Journal of Computational Physics, 126, (1996), pp (6) X. Deng and H. Zhang, Developing high-order weighted compact nonlinear schemes, Journal of Computational Physics, 165, (2), pp (7) T. Nonomura and K. Fujii, Robust eplicit formulation of weighted compact scheme, Computers & Fluids, 85, (213), pp (8) 㣤 ሯ,, " ༢ ㄪ ᛶ ᣢ ࡋ ࡓ 㸰 ḟ ᗘ Residual Distribution ἲ ࡘ," 14 ᅇ ὶయຊᏛࢩ ࢪ, (2), E3-3. (9) E. F. Toro, Riemann solvers and numerical methods for fluid dynamics: A practical introduction (3rd edition), Springer, (29). Fig. 7 Schematic diagram of Schardin s problem(2). Fig. 8 Numerical shadowgraph image at t=138psec.
5 第 46 回流体力学講演会 / 第 32 回航空宇宙数値シミュレーション技術シンポジウム論文集 155 Fig.9 Snapshots of density distribution for Schardin s problem.
: u i = (2) x i Smagorinsky τ ij τ [3] ij u i u j u i u j = 2ν SGS S ij, (3) ν SGS = (C s ) 2 S (4) x i a u i ρ p P T u ν τ ij S c ν SGS S csgs
![: u i = (2) x i Smagorinsky τ ij τ [3] ij u i u j u i u j = 2ν SGS S ij, (3) ν SGS = (C s ) 2 S (4) x i a u i ρ p P T u ν τ ij S c ν SGS S csgs](/thumbs/91/106610562.jpg ": u i = (2) x i Smagorinsky τ ij τ [3] ij u i u j u i u j = 2ν SGS S ij, (3) ν SGS = (C s ) 2 S (4) x i a u i ρ p P T u ν τ ij S c ν SGS S csgs")
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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,, Department of Civil Engineering, Chuo University Kasuga 1-13-27, Bunkyo-ku, Tokyo 112 8551, JAPAN E-mail : atsu1005@kc.chuo-u.ac.jp E-mail : kawa@civil.chuo-u.ac.jp SATO KOGYO CO., LTD. 12-20, Nihonbashi-Honcho
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Fig. 1 The scheme of glottal area as a function of time Fig. 3 Flow diagram of image processing. Black rectangle in the photo indicates the processing area (128 x 32 pixels). Fig, 4 Parametric representation
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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 Date 2017 URL http://hdl.handle.net/2433/229150 Right
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