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  • 1
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    Transonic viscous-inviscid interaction using Euler and inverse boundary-layer equations (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The paper is concerned with the use of a zonal method for the computation of transonic viscous-inviscid interacting flow about airfoils. The inviscid portion of the flow is treated by using an Euler equation solution method, while an inverse integral compressible turbulent boundary-layer solution method is used for the viscous portion of the flow. The matching of the viscous and inviscid solutions is discussed, and some numerical results as well as comparisons with experimental data are presented.
    Keywords: AERODYNAMICS
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  • 2
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    Computation of transonic viscous-inviscid interacting flow (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Transonic viscous-inviscid interaction is considered using the Euler and inverse compressible turbulent boundary-layer equations. Certain improvements in the inverse boundary-layer method are mentioned, along with experiences in using various Runge-Kutta schemes to solve the Euler equations. Numerical conditions imposed on the Euler equations at a surface for viscous-inviscid interaction using the method of equivalent sources are developed, and numerical solutions are presented and compared with experimental data to illustrate essential points. Previously announced in STAR N83-17829
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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  • 3
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    Multigrid acceleration of the flux split Euler equations (1986)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Multigrid acceleration is applied to a flux-split algorithm for solving the Euler equations in two and three dimensions. The basic algorithm is an implicit spatially-split approximate factorization method. The stability of the scheme in comparison to other factorization is examined. Results are presented for two-dimensional airfoil flows and three-dimensional wing flows which demonstrate substantially improved convergence with the multigrid algorithm. An asymptotic spectral radius of 0.89 and 0.93 is attained for a 97 x 17 x 17 wing solution at subcritical and supercritical conditions, respectively.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-0274
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  • 4
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    Three-dimensional unsteady Euler equations solutions on dynamic grids (1985)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: A method is presented for solving the three-dimensional unsteady Euler equations on dynamic grids based on flux vector splitting. The equations are cast in curvilinear coordinates and a finite volume discretization is used for handling arbitrary geometries. The discretized equations are solved using an explicit upwind second-order predictor corrector scheme that is stable for a CFL of 2. Characteristic variable boundary conditions are developed and used for unsteady impermeable surfaces and for the far-field boundary. Dynamic-grid results are presented for an oscillating air-foil and for a store separating from a reflection plate. For the cases considered of stores separating from a reflection plate, the unsteady aerodynamic forces on the store are significantly different from forces obtained by steady-state aerodynamics with the body inclination angle changed to account for plunge velocity.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 85-1704
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  • 5
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    Three-dimensional unsteady Euler equation solutions using flux vector splitting (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A method for numerically solving the three dimensional unsteady Euler equations using flux vector splitting is developed. The equations are cast in curvilinear coordinates and a finite volume discretization is used. An explicit upwind second-order predictor-corrector scheme is used to solve the discretized equations. The scheme is stable for a CFL number of two and local time stepping is used to accelerate convergence for steady-state problems. Characteristic variable boundary conditions are developed and used in the far field and at surfaces. No additional dissipation terms are included in the scheme. Numerical results are compared with results from an existing three dimensional Euler code and experimental data.
    Keywords: NUMERICAL ANALYSIS
    Type: NASA-CR-173254 , NAS 1.26:173254
    Format: application/pdf
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  • 6
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    Three-dimensional unsteady Euler solutions for propfans and counter-rotating propfans in transonic flow (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An Euler code designed for computing the unsteady, three-dimensional, transonic flow about single-rotating and counter-rotating propfans using dynamic blocked-grids is presented. The algorithm is a finite volume, flux-split, upwind, implicit scheme and solves the equations which have been written in a time-dependent curvilinear coordinate system. Relative motion of the blades for counter-rotating configurations is handled by requiring that grid lines be aligned after each discrete rotation of fore and aft rotor grid blocks. The method by which information is passed across block interfaces, as well as how downstream characteristic outflow boundary conditions which enforce simple radial equilibrium are implemented, is discussed. Comparisons of computed flow-field parameters and propfan performance with experimental data indicate good overall agreement between predictions and measurements.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-1197
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  • 7
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    Computation of transonic viscous-inviscid interacting flow (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Transonic viscous-inviscid interaction is considered using the Euler and inverse compressible turbulent boundary-layer equations. Certain improvements in the inverse boundary-layer method are mentioned, along with experiences in using various Runge-Kutta schemes to solve the Euler equations. Numerical conditions imposed on the Euler equations at a surface for viscous-inviscid interaction using the method of equivalent sources are developed, and numerical solutions are presented and compared with experimental data to illustrate essential points.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-85203 , NAS 1.15:85203
    Format: application/pdf
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  • 8
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    Three-dimensional unsteady Euler equations solution using flux vector splitting (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A method for numerically solving the three-dimensional unsteady Euler equations using flux vector splitting is developed. The equations are cast in curvilinear coordinates and a finite volume discretization is used. An explicit upwind second-order predictor-corrector scheme is used to solve the discretized equations. The scheme is stable for a CFL number of 2 and local time stepping is used to accelerate convergence for steady-state problems. Characteristic variable boundary conditions are developed and used in the far-field and at surfaces. No additional dissipation terms are included in the scheme. Numerical results are compared with results from an existing three-dimensional Euler code and experimental data.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-1552
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  • 9
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    Viscous-inviscid interaction computations using a pseudo Navier-Stokes approach (1985)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A new method is presented for the computation of viscous-inviscid interaction. The idea is to treat rotational inviscid flow (of which flows are almost entirely composed) in a thorough manner, and accept an approximation treatment of vorticity as introduced by viscous effects. The approach is to numerically solve the Navier-Stokes equations with the viscous terms determined from an inverse boundary-layer solution. The method falls somewhere between a Navier-Stokes approach and an Euler and boundary-layer equation coupling approach; consequently, it is referred to as a pseudo Navier-Stokes approach. Results from both the Navier-Stokes equations and the pseudo Navier-Stokes approach are presented.
    Keywords: AERODYNAMICS
    Type: Symposium on Numerical and Physical Aspects of Aerodynamic Flows; Jan 21, 1985 - Jan 24, 1985; Long Beach, CA
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