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  • Fluid Mechanics and Thermodynamics  (4)
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  • 1
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    An Implicit Upwind Algorithm for Computing Turbulent Flows on Unstructured Grids (1994)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: An implicit, Navier-Stokes solution algorithm is presented for the computation of turbulent flow on unstructured grids. The inviscid fluxes are computed using an upwind algorithm and the solution is advanced in time using a backward-Euler time-stepping scheme. At each time step, the linear system of equations is approximately solved with a point-implicit relaxation scheme. This methodology provides a viable and robust algorithm for computing turbulent flows on unstructured meshes. Results are shown for subsonic flow over a NACA 0012 airfoil and for transonic flow over a RAE 2822 airfoil exhibiting a strong upper-surface shock. In addition, results are shown for 3 element and 4 element airfoil configurations. For the calculations, two one equation turbulence models are utilized. For the NACA 0012 airfoil, a pressure distribution and force data are compared with other computational results as well as with experiment. Comparisons of computed pressure distributions and velocity profiles with experimental data are shown for the RAE airfoil and for the 3 element configuration. For the 4 element case, comparisons of surface pressure distributions with experiment are made. In general, the agreement between the computations and the experiment is good.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Computers Fluids; Volume 23; No. 1; 1-21
    Format: application/pdf
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  • 2
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    A Boundary Condition for Simulation of Flow Over Porous Surfaces (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A new boundary condition is presented.for simulating the flow over passively porous surfaces. The model builds on the prior work of R.H. Bush to eliminate the need for constructing grid within an underlying plenum, thereby simplifying the numerical modeling of passively porous flow control systems and reducing computation cost. Code experts.for two structured-grid.flow solvers, TLNS3D and CFL3D. and one unstructured solver, USM3Dns, collaborated with an experimental porosity expert to develop the model and implement it into their respective codes. Results presented,for the three codes on a slender forebody with circumferential porosity and a wing with leading-edge porosity demonstrate a good agreement with experimental data and a remarkable ability to predict the aggregate aerodynamic effects of surface porosity with a simple boundary condition.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: AIAA Paper 2001-2412 , 19th Applied Aerodynamics Conference; Jun 11, 2001 - Jun 14, 2001; Anaheim, CA; United States
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  • 3
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    Implicit/Multigrid Algorithms for Incompressible Turbulent Flows on Unstructured Grids (1997)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: An implicit code for computing inviscid and viscous incompressible flows on unstructured grids is described. The foundation of the code is a backward Euler time discretization for which the linear system is approximately solved at each time step with either a point implicit method or a preconditioned Generalized Minimal Residual (GMRES) technique. For the GMRES calculations, several techniques are investigated for forming the matrix-vector product. Convergence acceleration is achieved through a multigrid scheme that uses non-nested coarse grids that are generated using a technique described in the present paper. Convergence characteristics are investigated and results are compared with an exact solution for the inviscid flow over a four-element airfoil. Viscous results, which are compared with experimental data, include the turbulent flow over a NACA 4412 airfoil, a three-element airfoil for which Mach number effects are investigated, and three-dimensional flow over a wing with a partial-span flap.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: AIAA Paper 95-1740
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  • 4
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    Navier-Stokes Computations and Experimental Comparisons for Multielement Airfoil Configurations (1993)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A two-dimensional unstructured Navier-Stokes code is utilized for computing the flow around multielement airfoil configurations. Comparisons are shown for a landing configuration with an advanced-technology flap. Grid convergence studies are conducted to assess inaccuracies caused by inadequate grid resolution. Although adequate resolution is obtained for determining the pressure distributions, further refinement is needed to sufficiently resolve the velocity profiles at high angles of attack. For the advanced flap configuration, comparisons of pressure distributions and lift are made with experimental data. Here, two flap riggings and two Reynolds numbers are considered. In general, the trends caused by variations in these quantities are well predicted by the computations, although the angle of attack for maximum lift is overpredicted.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: AIAA Paper 93-0645 , Aerospace Sciences Meeting; Jan 01, 1993; Reno, NV; United States
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