Simulation of transonic separated airfoil flow by finite-difference viscous-inviscid interaction

Dalsem, W. R. Van; Steger, J. L.

doi:10.1007/3-540-13917-6_203

Cited by 6 publications

(4 citation statements)

References 5 publications

(3 reference statements)

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“…For mildly separated transonic flow, it can provide very good results. 12 ' 13 However, the range of allowable blowing rates is more restricted for the IBL procedure than for the TLNS approach. In addition, the steady first-order boundary-layer approximation becomes suspect when a strong shock and boundary-layer interaction occurs, because dp/dy in the boundary layer may not be negligible.…”

Section: Tlns Proceduresmentioning

confidence: 99%

“…The transonic airfoil (TAIR) full-potential code was developed by Hoist 10 and Dougherty et al 11 The present boundary-layer and viscous-inviscid interaction algorithms were developed by Van Dalsem 12 and Van Dalsem and Steger. 13 The major modifications required for this work are associated with the boundary-layer forcing function, the boundary-condition treatment, the viscous-inviscid interaction algorithm, and the turbulence model.…”

Section: Ibl Proceduresmentioning

confidence: 99%

“…Grid points are clustered near the wall and wake centerline. 12 The inviscid grid size is 223 x 31, with additional 50 grid lines in the r/ direction for the boundary-layer algorithm. In the TLNS procedure, a C-type 251 x 65 grid is generated by solving hyperbolic equations.…”

Section: Grid Generationmentioning

confidence: 99%

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Computation of viscous transonic flow over porous airfoils

Chen

Chow

Dalsem

et al. 1989

Journal of Aircraft

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The viscous effects on transonic flow past an airfoil that contains a shallow cavity beneath a porous surface are studied numerically. The porous region occupies a small portion of the total airfoil surface and is located near the shock. Both an interactive boundary-layer (IBL) algorithm and a thin-layer Navier-Stokes (TLNS) algorithm have been modified for use in studying the outer flow, whereas a stream-function formulation has been used to model the inner flow in the small cavity. The coupling procedure at the porous surface is based on Darcy's law and on the assumption of a constant total pressure in the cavity. In addition, a modified Baldwin-Lomax turbulence model is used to consider the transpired turbulent bounday layer in the TLNS approach, and the Cebeci-Smith turbulence model is used in the IBL approach. According to the present analysis, a porous surface can reduce the wave drag appreciably, but it can also increase viscous losses. As has been observed experimentally in nonlifting airfoils, the numerical results indicate that the total drag may be reduced at higher Mach numbers and increased at lower Mach numbers. Furthermore, the streamline patterns of passive-shock and boundarylayer interaction are revealed in this study.

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Section: Tlns Proceduresmentioning

confidence: 99%

Section: Ibl Proceduresmentioning

confidence: 99%

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Computation of viscous transonic flow over porous airfoils

Chen

Chow

Dalsem

et al. 1989

Journal of Aircraft

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“…Since that time, several improved codes have been developed that can do the calculations in either direct or inverse mode (Carter 1974, Klineberg and Steger 1974, Van Dalsem and Steger 1983. Carter (1979Carter ( , 1981, Van Dalsem and Steger (1983), Van Dalsem (1984), and Steger and Van Dalsem (1985) have interacted their codes with full-potential codes to achieve complete viscous-in.viscid interaction. Steger and Van Dalsem (1985) also interacted their boundary layer code with a vector-potential code allowing rotational flow and convection of entropy, which improved the shock capturing capabilities of the scheme.…”

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confidence: 99%

A truncation error injection approach to viscous-inviscid interaction

Goble

Fung

1987

25th AIAA Aerospace Sciences Meeting

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Porous aerofoil analysis using viscous‐inviscid coupling at transonic speeds

Olling

Dulikravich²

1987

Numerical Methods in Fluids

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SUMMARYViscous-inviscid interaction is used to compute steady two-dimensional, transonic flows for solid and porous aerofoils. A full-potential code was coupled with both a laminar/transition/turbulent integral boundarylayer/turbulent wake code and the finite-difference boundary-layer code using the semi-inverse methods of Carter and Wigton. The coupling was performed using the transpiration coupling concept, thus allowing for analysis of porous aerofoils with passive physical transpiration. The computations confirm experimental findings that passive physical transpiration can lead to a lower drag coefficient and a higher lift coefficient, a weaker shock and elimination of shock-induced separation. Nevertheless, it is very important that the extent of the porous region and permeability factor distribution of the porous region are chosen carefully if these improvements are to be achieved.

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Simulation of transonic separated airfoil flow by finite-difference viscous-inviscid interaction

Cited by 6 publications

References 5 publications

Computation of viscous transonic flow over porous airfoils

Computation of viscous transonic flow over porous airfoils

A truncation error injection approach to viscous-inviscid interaction

Porous aerofoil analysis using viscous‐inviscid coupling at transonic speeds

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