An interaction model for the solution of                                                   laminar separation on a surface

Miller, George E.; Fanchiotti, Aldo

doi:10.2514/6.1975-5

13th Aerospace Sciences Meeting 1975

DOI: 10.2514/6.1975-5

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An interaction model for the solution of laminar separation on a surface

George E. Miller¹,

Aldo Fanchiotti²

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1979

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“…Such problems have been circumvented in recent extensions of the Ferri-Dash procedure by splitting the axial pressure gradient term and desensitizing the normal velocity computation (see [3, 4 and 5]) for cases with negligible upstream influence. An extension of the Ferri-Dash procedure to analyze problems with significant upstream influence is discussed in [6]. While the authors deem it more economical to use fully elliptic procedures for strongly interactive cases, most recent work in this area (see [7, 8 and 9]) has not been so formulated.…”

mentioning

confidence: 99%

Closure to “Discussion of ‘A Hybrid Marching Integration Procedure for the Prediction of Two-Dimensional Supersonic Boundary Layers’” (1979, ASME J. Fluids Eng., 101, p. 400)

Issa¹,

Lockwood²

1979

Journal of Fluids Engineering

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The hybrid marching integration procedure presented by the authors is quite analagous to the earlier approach of Ferri and Dash [1, 2]. Both models: divide the viscous domain into subsonic and supersonic regions; solve the parabolic boundary layer equations in the subsonic region by an implicit finite-difference procedure; solve the hyperbolic/parabolic flow equations in the supersonic region by a viscous-characteristic procedure, and; match the two solutions in the vicinity of the sonic line. In the Ferri-Dash approach, the subsonic and supersonic solutions are fully coupled by requiring the continuity of all flow variables at the matching point. This is accomplished by retention of the normal momentum equation in the subsonic region and the performance of an iterative matching in the vicinity of the sonic line wherein the key interactive parameter is the normal component of velocity. In the authors' method, the variation in the normal velocity component across the subsonic region is neglected (i.e., the wall angle is imposed at the sonic point). This, in effect, completely decouples the subsonic and supersonic solutions and cannot be regarded as a true interactive procedure.The authors neglect of flow angle variation was motivated by stability problems encountered in attempting to include this effect. Such problems have been circumvented in recent extensions of the Ferri-Dash procedure by splitting the axial pressure gradient term and desensitizing the normal velocity computation (see [3, 4 and 5]) for cases with negligible upstream influence. An extension of the Ferri-Dash procedure to analyze problems with significant upstream influence is discussed in [6]. While the authors deem it more economical to use fully elliptic procedures for strongly interactive cases, most recent work in this area (see [7, 8 and 9]) has not been so formulated.

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mentioning

confidence: 99%

Closure to “Discussion of ‘A Hybrid Marching Integration Procedure for the Prediction of Two-Dimensional Supersonic Boundary Layers’” (1979, ASME J. Fluids Eng., 101, p. 400)

Issa¹,

Lockwood²

1979

Journal of Fluids Engineering

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An interaction model for the solution of laminar separation on a surface

Cited by 1 publication

References 0 publications

Closure to “Discussion of ‘A Hybrid Marching Integration Procedure for the Prediction of Two-Dimensional Supersonic Boundary Layers’” (1979, ASME J. Fluids Eng., 101, p. 400)

Closure to “Discussion of ‘A Hybrid Marching Integration Procedure for the Prediction of Two-Dimensional Supersonic Boundary Layers’” (1979, ASME J. Fluids Eng., 101, p. 400)

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