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

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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 ✬ ✫ EFERENCES Chawal M. D., Edwards L. C. and Franke M, E 1990 Wind Tunnel Investigation of Wing –in Ground Effect, Journal of Aircraft, Vol 27 ,No.4, pp.289-293 Chorin A. J., 1967 A Numerical Method for Solving Incompressible Viscous Flow Problems, Journal Computational Physics Vol.2 No.2, pp,14-23 Chun H. H., Chang C. H. and Paik K. J.,1999, Longitudinal Stability of a Wing in Ground Effect Craft, J. of The Society of Naval Architects of Korea, Vol.36,No.3,pp.60-70 RINA, London, U., total of 19 papers include machines 2000, Saint Petersburg State Marine Technical University , Russia Sowdon A., 1995 A Simple Method to remove the Boundary Layer on a Ground Plate, Papers of Ship Research Institute Japan , Vol.32 Vo.2, pp. 53-78 Stinton D. 1998 The Anatomy of the Aeroplan , 2nd Edition published Blacewell Science, pp. 86-92 Staufenbiel, D, 1996 Comment on Aerodynamic Characteristics of a Two Dimensional Airfoil with Ground Effect, Journal of Aircraft Aerodynamic of Wing-In-Ground Effect Vehicles Rheinisch-West-falische Technische Hochschule, project Rept. 78/1, Aachen, Germany, 1978 Steinbach, D 1996 Comment on Aerodynamic Characteristics of a Two-Dimensional Airfoil with Ground Effect , Journal of Aircraft, Vol.34, No.3, pp.455-456 Thomas J. L., Paulson J,w. and Margason R, J., 1979 Powered Low-Aspect-ratio Wing in Ground Effect (WIG) Aerodynamic Characteristics, NASA TM78793 Turner T. R., 1966 Endless-Belt Technique for Ground Simulation, NASA SP-116 Speziale, C.G., Abid, R. & Anderson, E.C. 1992, .Critical Evaluation of Two-Equation Models for Near-Wall Turbulence., AIAA J., Vol. 30 No. 2, pp. 324-331. Wilcox, D.C. 1988, .Reassessment of the scaledetermining equation for advanced turbulence models., AIAA J., Vol. 26 No. 11, pp. 1299- 1310. Pajayakrit, P. & Kind, R.J. 2000, .Assessment and Modification of Two-Equation Turbulence Models., AIAA J., Vol. 38 No. 6, pp. 955-963. Gorski, J. & Nguyen, P. 1991, .Navier-Stokes Analysis of Turbulent Boundary Layer Wake for Two-Dimensional Lifting Bodies.,Eighteenth Symposium on Naval Hydrodynamics, Ann Abor, USA, pp. 633-643. Gersten, K. & Schlichting, H. 2000, .Boundary Layer Theory., 8th Ed., Springer-Verlag, Berlin, Germany. Abbott, I.H., and von Doenhoff, A.E., Theory of Wing Sections, Dover, New York, 1959. Akimoto, H. and Kubo, S., 1998 Characteristics Study of Twp-dimensional in Surface Effect by CFD Simulation, Journal of the Society of Naval Architects of Japan, Vol. 184,pp.a7-54 Bagley J. A., 1961 The Pressure Distribution on Two-Dimensional Wings Near Ground, Ministry of Aviation Aeronautical Research Council R&M, NO,3238,40 pages Chang R, H 2000 Numerical Simulation of Turbulent Flow around Two-Dimensional Wings In Ground Effect Wing Different Ground Boundary Condition, MSc Thesis, Dept of Naval Architecture & ocean Engineering Pusan National University, Korea Speaker: FIROOZ, A. 84 BAIL 2006 ✩ ✪
S.A. GAPONOV, G.V. PETROV, B.V. SMORODSKY: Boundary layer intercation with external disturbances ✬ ✫ BOUNDARY LAYER INTERACTION WITH EXTERNAL DISTURBANCES S.A.Gaponov, G.V.Petrov, B.V.Smorodsky Institute of Theoretical and Applied Mechanics SB RAS, Novosibirsk 630090, Russia; E-mail: gaponov@itam.nsc.ru, Fax:+7(3832)342268 Generation of initial unstable eigen disturbances inside the boundary layer (BL) by external perturbations is an actual problem nowadays in the investigation of laminar-turbulent transition. Morkovin [1] was the first who has formulated so called BL receptivity problem. Up to now a lot of experimental and theoretical works studying subsonic BL has been performed. The detailed review of these efforts can be found in [2,3]. The knowledge about the supersonic BL is much shorter at the present moment. The existing papers are devoted mainly to the investigation of external acoustic field interaction with a supersonic BL on a smooth flat plate [4-6]. However an oncoming supersonic flow always comprises not only acoustic but also vortical and thermal (entropy) perturbations [7]. This paper presents results concerning irrotational external disturbances with zero damping in the direction of the main flow. Present paper is devoted to the investigation of disturbance excitation in sub- and supersonic BL by external vortical and thermal waves. Interaction of the acoustic waves with the BL on the non-smooth surface has also been investigated and is reported here.Studies were conducted both in an approaching of parallel basic flow and taken in consideration dependence of the main flow in boundary layer on longitudinal coordinate. In the second case were used of an equation of stability offered in [8]. For the acoustic field we distinguish two different kinds of interaction with the BL. In the first case the incidence angle of the acoustic wave onto the BL is finite. In the second case the incidence angle is zero. If the incidence angle is equal to zero, then in the result of the interaction the normal to the-wall disturbance velocity at the BL outer edge is non-zero and it is an additional source of the streamwise acoustic field. Such interaction leads to a very fast amplification of initial wave. For nonzero incidence angles we have performed computations of the reflection coefficient. It is important to note here that in some cases such reflectance is greater than unity. The amplitude of mass flux perturbation inside the BL excited by an external acoustic wave is practically always an order of magnitude larger than the initial wave amplitude in the free stream. Comparison of theoretical results with the experiment [6] leads authors to necessary to consider the problem of diffraction of acoustic waves on a plate leading edge. Using Fourier transformation and the equations of gas dynamics, one can show, that mass flux fluctuations along the plate could be completely determined by means of the jump of normal-to-thewall disturbance velocity at the plate leading edge. The normal velocity disturbance upstream of the plate leading edge ( x < 0 ) is determined by the distribution of the mass flux. The obtained formulas give the relations of the mass flux in the region x > 0 with its distribution at x < 0 . It was shown that intensity of the mass flux fluctuation is reduced with distance from the leading edge and is dependent of the orientation of the incident wave. Tollmien-Schlichting (TS) wave excitation in the supersonic BL by a pair of acoustic waves has been also investigated theoretically. The receptivity coefficient and the range of wave parameters where TS-wave generation takes place have been computed. It was obtained, that at enough large values of a Reynold's number, in narrow range of the acoustic wave numbers, the excited disturbances practically do not differ from an own increasing disturbance. Outside of this range the TS wave is not excited. The parameters of excited disturbances hardly differ from TS wave parameters near a neutral point, the coincidence is observed only at essential move away from neutral area downstream Beside in the paper investigation of the sound interaction with BL on the flat plate with roughness is consider also. The problem of the disturbance generation by small amplitude spatially periodic wall roughness has been formulated and solved in the linear approximation. The parameters of sound irradiated by the model with roughness in the supersonic flow have been computed. The peculiarities of the disturbances in the case when the angle between the wave fronts and the mean flow is close to the Mach angle have been investigated specially. It has been shown that the amplitude of the disturbance streamline inside the BL is greatly reduced in the near-wall sub-layer. At M = 1 mass flux perturbations in the main part of the BL are close to zero also. Considerable reduction of the Speaker: GAPONOV, S.A. 85 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
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W. LAYTON, I. STANCULESCU: Numerica
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H. WANG: A Component-Based Eulerian
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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
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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 102 and 103: B. EISFELD: Computation of complex
Page 104 and 105: 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
Page 152 and 153: N. PARUMASUR, J. BANASIAK, J.M. KOZ
Page 154 and 155: 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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