Euler calculations for wing-alone configuration

Ruo, S. Y.; Sankar, Lakshmi N.

doi:10.2514/3.45600

Cited by 8 publications

(3 citation statements)

References 6 publications

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“…A variety of methods has been devised to take the body dynamics into account. Magnus and Yoshihara 1 as well as Ruo and Sankar 18 have circumvented the problem of an unsteady grid by specifying time-dependent transpiration velocities to simulate airfoil oscillations. Rigid airfoil oscillations have been studied with a rigidly moving grid 49 and with a deforming grid.…”

Section: Pmentioning

confidence: 99%

Conservative multiblock Navier-Stokes solver for arbitrarily deforming geometries

Hoffren¹,

Siikonen²,

Laine³

1995

Journal of Aircraft

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A new finite volume based thin-layer Navier-Stokes solver for time-dependent compressible flows is described. The implicit, temporally and spatially second-order accurate formulation facilitates the simulation of flows at high Reynolds numbers. Complex, arbitrarily deforming geometries can be handled using fully conservative multiblock structured grids. An iterative time-stepping utilizing a multigrid technique maintains the temporal and spatial accuracy of the basic scheme also at grid block interfaces and solid boundaries. Several test cases have been computed to verify the proper function of the developed code, and the simulations of a transonic buffet and an oscillating supercritical airfoil are presented here. The solver employing the three-level fully implicit time discretization scheme is found to work well in dynamic grids within the limitations of the original formulation. The new code has the desired capabilities, although there is room for improvement in computational efficiency. Nomenclaturerea l P art °f scaled unsteady pressure coefficient, 2;jsin(ft>OCp(Od'/Kr) c = airfoil chord c d , c, = drag and lift coefficients e = total energy per unit volume F = flux vector in a curvilinear grid k = reduced frequency, a>c/(2f/ ao ) M = Mach number n v , n v = Cartesian unit normal components of a cell face p = pressure R = residual Re = Reynolds number S = cell face area T = cycle period t -time U = vector of conservative variables U x -freestream velocity u = convective velocity component u, v = Cartesian velocity components u g , v g = Cartesian velocity components of the grid u n = normal velocity component of the flow V = cell volume v n = normal velocity component of the grid jc, y = spatial coordinates a = instantaneous angle of attack, a + « 0 sin(W) a = average angle of attack a () = angle-of-attack oscillation amplitude ft = parameter defining the implicitness of the temporal discretization y = parameter controlling the time levels in the temporal discretization A/ = physical time step, nondimensionalized by the freestream sonic speed and the airfoil chord AT = volume swept by a cell face during a time step AT = local pseudo-time-step 8U = change in conservative variables in an iteration cycle or a pseudo-time-step p = density a> = angular velocity Subscripts /, j = spatial indices k = summing index mod = modified expression v = viscous 1,2 = cell face endpoints Superscripts k = intermediate solution between n and n + 1 n = time level with the latest known solution n + 1 = new time level with the unknown solution n -1 = time level one step before n

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Section: Pmentioning

confidence: 99%

Conservative multiblock Navier-Stokes solver for arbitrarily deforming geometries

Hoffren¹,

Siikonen²,

Laine³

1995

Journal of Aircraft

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“…The technique is also often used for boundary layer patching with inviscid flow techniques. Also more recently, the technique has been used to simulate surface deformations in full potential solution techniques, in addition to steady and unsteady rigid-body applications with Euler codes [3][4][5][6][7][8][9][10] .…”

Section: Introductionmentioning

confidence: 99%

Application of the transpiration method for aeroservoelastic prediction using CFD

Stephens

Arena

Gupta

1998

39th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and Exhibit

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Research presented in this paper illustrates the implementation of the transpiration boundary condition in steady and unsteady aeroelastic and aeroservoelastic simulations. For two reference cases, the AGARD 445.6 wing and the BACT wing with a finite-span flap, application of the transpiration method has demonstrated the effectiveness of applying the transpiration boundary condition at a variety of Mach numbers on configurations of practical interest. Additionally, the effectiveness of the transpiration method is demonstrated by its ability to model large scale continuous and discontinuous surface deflections without the computational expense of re-meshing at each CFD time-step. Nomenclature CFD Computational Fluid Dynamics M Mach Number ASE Aeroservoelasticity C P Pressure Coefficient α Angle of Attack (deg) δ Control Surface Deflection (deg) q Generalized Displacement Φ Modal Displacement Matrix η Generalized Displacement Vector

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“…This method is then applied on the hybrid-unstructured mesh of Onera M6 wing [4]. Also the computational static aeroelastic analysis was carried out for the high aspect ratio LANN wing [5] to validate the computational results. Latter Sections will cover the CFD and CSD solvers, RBF formulation and CFD/CSD coupling procedure.…”

mentioning

confidence: 99%

Aerodynamic and Static Aeroelastic Analysis of a Transonic Wing using Hybrid Unstructured Flow Solver

2014

International Conference on Innovative Engineering Technologies (ICIET’2014) Dec. 28-29, 2014 Bangkok (Thailand)

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Recent development of efficient numerical algorithms and availability of fast computational machines enables us to predict the static aeroelastic simulations more accurately. In order to establish confidence and quantify the results of these simulations, validation process should be conducted to ensure the accuracy of these results. In the present work, Steady Aerodynamic Analysis and Static Aeroelastic Simulations of Transonic Wing were carried out by using Hybrid Unstructured Navier-Stokes Flow Solver (HUNS3D). This CFD Code was developed in-house and coupled with an open source available CSD Solver (CalculiX). Loosely coupled approach was adopted for the coupling methodology. Multivariate data interpolation based on Radial Basic Function (RBF) scheme was adopted for the deformation of volume mesh. This procedure will ensure the coupled CFD/CSD solver accuracy and its ability to replicate the flow physics. The results were compared with the available experimental data, which shows good agreement between simulated and experimental results.

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Euler calculations for wing-alone configuration

Cited by 8 publications

References 6 publications

Conservative multiblock Navier-Stokes solver for arbitrarily deforming geometries

Conservative multiblock Navier-Stokes solver for arbitrarily deforming geometries

Application of the transpiration method for aeroservoelastic prediction using CFD

Aerodynamic and Static Aeroelastic Analysis of a Transonic Wing using Hybrid Unstructured Flow Solver

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