Development of a Turbulent Wall-Function Based Viscous Cartesian-Grid Methodology

Lee, Jae-Doo; Ruffin, Stephen M.

doi:10.2514/6.2007-1326

Cited by 18 publications

(13 citation statements)

References 10 publications

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“…In the finite volume method or finite difference method, an interpolation must be set up to calculate the values at the reference point. For instance, based on the finite volume method, in the paper [37], the primitive variables at a reference point are interpolated from the primitive variables of the three closest neighbor cell centers using the linear interpolation. However, if an image point is used in DG method, a situation may be encountered where the image point may locate in the ghost cell itself.…”

Section: Boundary Treatmentmentioning

confidence: 99%

Positivity-Preserving Runge-Kutta Discontinuous Galerkin Method on Adaptive Cartesian Grid for Strong Moving Shock

Liu

Qiu

Goman

et al. 2016

Numer. Math. Theory Methods Appl.

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Abstract. In order to suppress the failure of preserving positivity of density or pressure, a positivity-preserving limiter technique coupled with h-adaptive Runge-Kutta discontinuous Galerkin (RKDG) method is developed in this paper. Such a method is implemented to simulate flows with the large Mach number, strong shock/obstacle interactions and shock diffractions. The Cartesian grid with ghost cell immersed boundary method for arbitrarily complex geometries is also presented. This approach directly uses the cell solution polynomial of DG finite element space as the interpolation formula. The method is validated by the well documented test examples involving unsteady compressible flows through complex bodies over a large Mach numbers. The numerical results demonstrate the robustness and the versatility of the proposed approach.

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Section: Boundary Treatmentmentioning

confidence: 99%

Positivity-Preserving Runge-Kutta Discontinuous Galerkin Method on Adaptive Cartesian Grid for Strong Moving Shock

Liu

Qiu

Goman

et al. 2016

Numer. Math. Theory Methods Appl.

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“…Inviscid analysis of the tension cone was performed using the NASCART-GT code developed at the Georgia Institute of Technology [8][9][10][11]. NASCART-GT is a solution-adaptive, Cartesiangrid-based analysis tool that provides automated generation of grids around axisymmetric, two-dimensional, or three-dimensional (3-D) geometries.…”

Section: A Code Overviewmentioning

confidence: 99%

Validation of Computational Analyses for Supersonic Tension Cone Static Aerodynamic Performance

Clark

Braun

Ruffin

2012

Journal of Spacecraft and Rockets

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The future design and development efforts of supersonic inflatable aerodynamic decelerators will rely heavily on computational analyses to accurately assess performance characteristics. Work was performed in validating multiple computational fluid dynamics codes for analysis of a supersonic tension-cone inflatable aerodynamic decelerator. Inviscid axisymmetric solutions were computed and matched measured forebody pressure distributions, whereas predicted aftbody pressures exhibited variability. Calculated drag coefficients were within 5% of the total drag. Inviscid analysis accurately predicted the shock curvature and location. Viscous analyses performed using an overset grid topology demonstrated close agreement in calculated surface pressures, including aftbody pressures, at Mach numbers up to 3.0 and angles of attack up to 20 deg. Accurate predictions of aerodynamic performance at Mach numbers above 3.5 required a shock-aligned grid to eliminate errors introduced as a result of shock-staircasing. Using the shock-aligned grids, it was determined that at higher Mach number and higher angle of attack the leeward region of the tension cone likely transitions to a turbulent boundary layer, ensuring that the flow remained attached through a strong adverse pressure gradient. An investigation of aerodynamic performance in a Martian environment showed small increases in forebody-only axial force and minor decreases in static stability.Nomenclature C A = axial force coefficient C D = drag coefficient C m = pitching moment coefficient C m = pitching moment slope coefficient C N = normal force coefficient C P = pressure coefficient k 1 = turbulent kinetic energy Re = Reynolds number l = laminar viscosity t = turbulent viscosity

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“…The NRR technique has been implemented and is presently being improved, tested and validated in two flow solvers: NASCART-GT 4,5,6,7,8,16,17 and Unified Flow Solver (UFS). 9,10 NASCART-GT is a solution adaptive, Cartesian-grid based flow solver developed by at Georgia Tech.…”

Section: Introductionmentioning

confidence: 99%

Implementation and Evaluation of Normal Ray Refinement Technique in Adaptive Cartesian Framework

Arslanbekov

Kolobov

Ruffin

et al. 2012

42nd AIAA Fluid Dynamics Conference and Exhibit

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This paper describes further enhancement of the Normal Ray Refinement (NRR) technique and its implementation in the adaptive Cartesian framework of the Unified Flow Solver (UFS). Brief introduction to the UFS Navier-Stokes (NS) solver with an Immersed Boundary Method (IBM) is given. Demonstrations are provided of NRR grid generation algorithms based on normal rays with constant and variable refinement on 2D and 3D shapes. Low-and high-order accuracy inter-ray communications methods are implemented in 2Dand results for different shapes are demonstrated and compared to solutions obtained with uniform boundary grids. Capabilities for adaptive normal ray placement are developed in 2D and 3D thus providing ways for NRR automation when fully implemented. Results of flow solution for 2D geometries with statically placed and adaptive normal ray placement show good agreement with uniform boundary layer results. Implementation of the basic framework for NRR over 3D shapes is described and examples are shown. In prior study, the NRR technique was shown to provide accurate prediction of incompressible, attached viscous flows. In the current study the NRR methodology, implemented in NASCART-GT solver, is shown to provide accurate prediction in supersonic flow and low-speed, separated flow around a circular cylinder. It is found that the NRR technique is robustly implementable in different frameworks and it offers significant advantages in terms of greatly reduced number of cells in boundary layers when using Cartesian grids.

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Development of a Turbulent Wall-Function Based Viscous Cartesian-Grid Methodology

Cited by 18 publications

References 10 publications

Positivity-Preserving Runge-Kutta Discontinuous Galerkin Method on Adaptive Cartesian Grid for Strong Moving Shock

Positivity-Preserving Runge-Kutta Discontinuous Galerkin Method on Adaptive Cartesian Grid for Strong Moving Shock

Validation of Computational Analyses for Supersonic Tension Cone Static Aerodynamic Performance

Implementation and Evaluation of Normal Ray Refinement Technique in Adaptive Cartesian Framework

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