BAIL 2006 Book of Abstracts - Institut für Numerische und ...

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B. EISFELD: Computation of complex compressible aerodynamic flows with a Reynolds stress turbulence model ✬ ✫ �� Speaker: EISFELD, B. 80 BAIL 2006 ✩ ✪
A. FIROOZ, M. GADAMI: Turbulence Flow for NACA 4412 in Unbounded Flow and Ground Effect with Different Turbulence Models and Two Ground Conditions: Fixed and Moving Ground Conditions ✬ ✫ Turbulence Flow for NACA 4412 in Unbounded Flow and Ground Effect with Different Turbulence Models and Two Ground Conditions: Fixed and Moving Ground Conditions Abdolhamid Firooz, Academic board (ahfirooz@hamoon.usb.ac.ir) Mojgan Gadami, B.S. student (mozhgan_gadami@yahoo.com) Mechanical Engineering Department, University of Sistan & Baloochestan, Zahedan, Iran. Abstarct In this paper, the turbulence fluid flow around a two dimensional 4412 airfoil on different angles of attack near and far from the ground with the RANS (Reynolds averaged Navier-stokes) equations is calculated. Realizable K−ε turbulence model with Enhanced wall treatment and Spalart-Allmaras model are used (Re=2 × 10 6 ). Equations are approximated by finite volumes method, and they are solved by segregated method. The second order upwind method is used for the convection term, also for pressure interpolation the PRESTO method is used, and the relation between pressure and velocity with SIMPLEC algorithm is calculated. The computational domain extended 3C upstream of the leading edge of the airfoil 5C, downstream from the trailing edge, and 4C above the pressure surface. Distance from below the airfoil was defined with H/C where C is chord, and H is ground distance to the trailing edge. Velocity inlet boundary condition was applied upstream with speed of (U ∞ =29.215) and outflow boundary condition was applied downstream. The pressure and suction side of the airfoil and above and below's boundaries of domain were defined independently with no slip wall boundary condition. Moving wall with speed of (U ∞ =29.215) for above, and fixed or moving wall for below the airfoil was used. An unstructured mesh arrangement with quadrilateral elements was adopted to map the flow domain in ground effect and unbounded flow. A considerably fine C-type mesh was applied to achieve sufficient resolution of the airfoil surface and boundary layer region. Particular attention was directed to an offset 'inner region' encompassing the airfoil, and also C-type mesh was applied on near the airfoil at above and bottom, which it’s domain depends on the H/C in ground effects condition. Continuing downstream from leading edge and continuing far from above the airfoil H-type mesh was applied. Distance from the wall-adjacent cells must be determined by considering the range over which the log-law is valid. The distance is usually measured in the wall unit, y + (= ρu τ y / µ ). By increasing the grid numbers and changing the type of arranging mesh, adapting, around the airfoil a proper y + value, is obtained, and with this value solution results have good agreement with experimental data. Fig (1), Fig (2). The aerodynamic characteristic of an airfoil in ground proximity is known to be much different from that of unbounded flow. The condition of the wind tunnel bottom, I. e., moving or fixed relative to the airfoil would influence the performance of the airfoil in ground effect. The presence of boundary layer when air is flowing over bottom of the wind tunnel would be different from the real situation for a flying WIG. Proper velocity in moving ground boundary condition is considered with moving ground, and boundary layer is considered with fixed ground, and in the moving ground the boundary layer's effect is omitted, and so is the proper velocity in the fix ground. A grid independence analysis was conducted using some meshes of varying cell number. Each mesh was processed using the Realisable K-ε turbulence model with Enhanced wall treatment and Spalart-Allmaras model. Application of each mesh generally produces accurate predictions of the lift coefficients with comparison to the experimental data. It can be seen that the error associated with the predicated lift coefficient decreases with mesh refinement. In order to validate the present numerical data the computational results for NACA 4412 in unbounded flow is compared with published numerical results and experimental data. Fig (3). Fig (4) shows Cp variation on surface of the airfoil at four relative ground high computed (α =8). As the Speaker: FIROOZ, A. 81 BAIL 2006 ✩ ✪
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BAIL 2006 International Conference
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Plenary Session 1 Session 2 Session
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Room School-Lab (SL) Room MPI Sessi
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Room School-Lab (SL) Room MPI Tuesd
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Room School-Lab (SL) Room MPI Minis
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Contents Greetings . . . . . . . .
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CONTENTS S. HEMAVATHI, S. VALARMATH
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CONTENTS G. LUBE: A stabilized fini
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Plenary Presentations
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P. HOUSTON: Discontinuous Galerkin
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M. STYNES: Convection-diffusion pro
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V. GRAVEMEIER, S. LENZ, W.A. WALL:
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Minisymposia
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R.K. DUNNE, E. O’RIORDAN, M.M. TU
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G.I. SHISHKIN: A posteriori adapted
Page 40 and 41:
W. LAYTON, I. STANCULESCU: Numerica
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H. WANG: A Component-Based Eulerian
Page 44 and 45:
R. HARTMANN: Discontinuous Galerkin
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V. HEUVELINE: On a new refinement s
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J.A. MACKENZIE, A. NICOLA: A Discon
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R. SCHNEIDER, P. JIMACK: Anisotropi
Page 53 and 54: Speaker: Debopam Das, Tapan Sengupt
Page 55 and 56: M.H. BUSCHMANN, M. GAD-EL-HAK: Turb
Page 57 and 58: A. NAYAK, D. DAS: Three-dimesnional
Page 59 and 60: J. HUSSONG, N. BLEIER, V.V. RAM: Th
Page 61 and 62: T.K. SENGUPTA, A. KAMESWARA RAO: Sp
Page 63 and 64: L. SAVIĆ, H. STEINRÜCK: Asymptoti
Page 65 and 66: G.I. Shiskin, P. Hemker Robust Meth
Page 67 and 68: D. BRANLEY, A.F. HEGARTY, H. PURTIL
Page 69 and 70: T. LINSS, N. MADDEN: Layer-adapted
Page 71 and 72: L.P. SHISHKINA, G.I. SHISHKIN: A Di
Page 73 and 74: I.V. TSELISHCHEVA, G.I. SHISHKIN: D
Page 75 and 76: S. HEMAVATHI, S. VALARMATHI: A para
Page 77 and 78: J. Maubach, I, Tselishcheva Robust
Page 79 and 80: M. ANTHONISSEN, I. SEDYKH, J. MAUBA
Page 81 and 82: S. LI, L.P. SHISHKINA, G.I. SHISHKI
Page 83 and 84: A.I. ZADORIN: Numerical Method for
Page 85 and 86: P. ZEGELING: An Adaptive Grid Metho
Page 87: Contributed Presentations
Page 90 and 91: F. ALIZARD, J.-CH. ROBINET: Two-dim
Page 92 and 93: TH. ALRUTZ, T. KNOPP: Near-wall gri
Page 94 and 95: M. BAUSE: Aspects of SUPG/PSPG and
Page 96 and 97: L. BOGUSLAWSKI: Sheare Stress Distr
Page 98 and 99: A.CANGIANI, E.H.GEORGOULIS, M. JENS
Page 100 and 101: C. CLAVERO, J.L. GRACIA, F. LISBONA
Page 104 and 105: A. FIROOZ, M. GADAMI: Turbulence Fl
Page 106 and 107: A. FIROOZ, M. GADAMI: Turbulence Fl
Page 108 and 109: S.A. GAPONOV, G.V. PETROV, B.V. SMO
Page 110 and 111: M. HAMOUDA, R. TEMAM: Boundary laye
Page 112 and 113: M. HAMOUDA, R. TEMAM: Boundary laye
Page 114 and 115: M. HÖLLING, H. HERWIG: Computation
Page 116 and 117: A.-M. IL’IN, B.I. SULEIMANOV: The
Page 118 and 119: W.S. ISLAM, V.R. RAGHAVAN: Numerica
Page 120 and 121: D. KACHUMA, I. SOBEY: Fast waves du
Page 122 and 123: A. KAUSHIK, K.K. SHARMA: A Robust N
Page 124 and 125: P. KNOBLOCH: On methods diminishing
Page 126 and 127: T. KNOPP: Model-consistent universa
Page 128 and 129: J.-S. LEU, J.-Y. JANG, Y.-C. CHOU:
Page 130 and 131: V.D. LISEYKIN, Y.V. LIKHANOVA, D.V.
Page 132 and 133: G. LUBE: A stabilized finite elemen
Page 134 and 135: H. LÜDEKE: Detached Eddy Simulatio
Page 136 and 137: K. MANSOUR: Boundary Layer Solution
Page 138 and 139: J. MAUSS, J. COUSTEIX: Global Inter
Page 140 and 141: O. MIERKA, D. KUZMIN: On the implem
Page 142 and 143: K. MORINISHI: Rarefied Gas Boundary
Page 144 and 145: A. NASTASE: Qualitative Analysis of
Page 146 and 147: F. NATAF, G. RAPIN: Application of
Page 148 and 149: N. NEUSS: Numerical approximation o
Page 150 and 151: M.A. OLSHANSKII: An Augmented Lagra
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N. PARUMASUR, J. BANASIAK, J.M. KOZ
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B. RASUO: On Boundary Layer Control
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H.-G. ROOS: A Comparison of Stabili
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B. SCHEICHL, A. KLUWICK: On Turbule
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O. SHISHKINA, C. WAGNER: Boundary a
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M. STYNES, L. TOBISKA: Using rectan
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P. SVÁ ˘CEK: Numerical Approximat
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N.V. TARASOVA: Full asymptotic anal
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C.H. TAI, C.-Y. CHAO, J.-C. LEONG,
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H. TIAN: Uniformly Convergent Numer
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ABOUTUNSTEADYBOUNDARYLAYERONADIHEDR
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A.E.P. VELDMANN: High-order symmetr
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Z.-H. YANG, Y.-Z. LI, Y. ZHU: Appli
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Q. YE: Numerical simulation of turb
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Participants
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Mrs.Maragatha Meenakshi Ponnusamy P
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Authors Alizard, F., 67 Alrutz, Th,
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