An Inverse Integral Computational Method for Compressible Turbulent Boundary Layers

Whitfield, David L.; Swafford, T. W.; Donegan, T. L.

doi:10.1007/978-3-642-81932-2_30

Cited by 13 publications

(3 citation statements)

References 4 publications

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“…Instead of evaluating such integrals numerically at each streamwise location, the calculation can be made using the correlation of D in terms of the local edge Mach number, shape factor and skin friction coefficient' 13 '. The result of using an analytical correlation as opposed to numerically evaluating Equation 6is an increase in speed of O (10).…”

Section: Viscous Methodsmentioning

confidence: 99%

Numerical predictions of transonic viscous flows around aerofoils through an Euler/boundary layer interaction method

1992

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A semi-inverse viscous/inviscid coupling technique for the calculation of compressible flows is presented. Euler equations in integral form are solved for the inviscid part and integral compressible boundary-layer equations in direct and inverse form are solved for the viscous one. Interaction is realised using the equivalent sources approach.The technique has been applied to the calculation of the aerodynamic characteristics of aerofoils both in cruise and take-off or landing configurations. To treat the complex geometries involved in the latter case, a multi-block approach, based on structured ‘H’ grid topology, has been developed and validated for different configurations.

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Section: Viscous Methodsmentioning

confidence: 99%

Numerical predictions of transonic viscous flows around aerofoils through an Euler/boundary layer interaction method

1992

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“…Equations 3 and 5 can be arranged to (Whitfield, et al, 1982 The boundary layer calculations are performed separately on the upper and lower airfoil surfaces. The stagnation point is located.…”

Section: Jnverse Solutionmentioning

confidence: 99%

“…One type of zonal method used for inviscid-viscous interaction is an inviscid flow solution method for the flow away from the body matched to a viscous or boundary layer flow solution method for the flow near the body. For steady airfoil calculations, extensive inviscid-viscous interaction methods have been developed, for example Whitfield, et al (1982). The boundary layer computational methods are either finite difference or integral methods.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear Separated Inviscid–Viscous Analysis of Oscillating Cascade Aerodynamics Using an Inverse Integral Method

Wolff

Fleeter

1997

Volume 4: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation;

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A mathematical model is developed to analyze the unsteady flow through an harmonically oscillating cascade of airfoils, including separated flow. The model incorporates an inverse integral boundary layer solution with the time–marching Euler analysis NPHASE. An embedded composite grid formulation is incorporated, specifically a deforming C–grid embedded in a Cartesian H–grid, thereby simplifying grid generation. To reduce computational requirements, Fourier series unsteady periodic boundary conditions are implemented. The integral turbulent boundary layer model is closed with steady correlations adopted in a quasi–steady manner. To couple the inviscid and viscous solutions, the viscous effect is modeled in the unsteady Euler solution in a quasi–steady manner by a transpiration boundary condition. An isolated airfoil is used to compare the steady interaction model with experimental data. Then a flat plate cascade is used to verify the unsteady flow solver with linear theory predictions. An experimental unsteady aerodynamics data set of a loaded cascade with separated meanflow executing torsional oscillations compared favorably with the analysis. The code is then utilized to study the effect of flow separation on the unsteady aerodynamics.

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Application of Interacting Boundary-Layer Theory in the Analysis of Transonic Shock Induced Separation

Edwards

Whitfield

Carter

1986

Turbulent Shear-Layer/Shock-Wave Interactions

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An Inverse Integral Computational Method for Compressible Turbulent Boundary Layers

Cited by 13 publications

References 4 publications

Numerical predictions of transonic viscous flows around aerofoils through an Euler/boundary layer interaction method

Numerical predictions of transonic viscous flows around aerofoils through an Euler/boundary layer interaction method

Nonlinear Separated Inviscid–Viscous Analysis of Oscillating Cascade Aerodynamics Using an Inverse Integral Method

Application of Interacting Boundary-Layer Theory in the Analysis of Transonic Shock Induced Separation

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