A viscous flow based membrane wing model

Richard Smith; Wei Shyy

doi:10.2514/6.1993-2955

A viscous flow based membrane wing model

Richard Smith, Wei Shyy

Research output: Contribution to conference › Conference Paper › peer-review

3 Citations (Scopus)

Abstract

A computational procedure has been developed which extends previous work on membrane wing aerodynamics to include the effects of viscosity in the fluid. The present membrane wing model is derived by combining an incremental, continuum based, finite element formulation of the elastic membrane problem with a control volume formulation of the Navier-Stokes equations written in general curvilinear body-fitted coordinates. The model yields solutions for membrane shape, membrane stress, and the surrounding viscous flow field variables simultaneously. The results of the viscous flow based model are qualitatively in agreement with flow visualization studies reported in the literature. The effect of viscosity in the fluid leads to substantially different membrane surface pressures compared with the surface pressures predicted by an inviscid flow model.

Original language	English
DOIs	https://doi.org/10.2514/6.1993-2955
Publication status	Published - 1993
Externally published	Yes
Event	AIAA 23rd Fluid Dynamics, Plasmadynamics, and Lasers Conference, 1993 - Orlando, United States Duration: 6 Jul 1993 → 9 Jul 1993

Conference

Conference	AIAA 23rd Fluid Dynamics, Plasmadynamics, and Lasers Conference, 1993
Country/Territory	United States
City	Orlando
Period	6/07/93 → 9/07/93

Bibliographical note

Publisher Copyright:
© 1993 by the American Institue of Aeronautics and Aerodynamics,Ilnc. All Rights reserved.

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title = "A viscous flow based membrane wing model",

abstract = "A computational procedure has been developed which extends previous work on membrane wing aerodynamics to include the effects of viscosity in the fluid. The present membrane wing model is derived by combining an incremental, continuum based, finite element formulation of the elastic membrane problem with a control volume formulation of the Navier-Stokes equations written in general curvilinear body-fitted coordinates. The model yields solutions for membrane shape, membrane stress, and the surrounding viscous flow field variables simultaneously. The results of the viscous flow based model are qualitatively in agreement with flow visualization studies reported in the literature. The effect of viscosity in the fluid leads to substantially different membrane surface pressures compared with the surface pressures predicted by an inviscid flow model.",

author = "Richard Smith and Wei Shyy",

note = "Publisher Copyright: {\textcopyright} 1993 by the American Institue of Aeronautics and Aerodynamics,Ilnc. All Rights reserved.; AIAA 23rd Fluid Dynamics, Plasmadynamics, and Lasers Conference, 1993 ; Conference date: 06-07-1993 Through 09-07-1993",

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language = "English",

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T1 - A viscous flow based membrane wing model

AU - Smith, Richard

AU - Shyy, Wei

PY - 1993

Y1 - 1993

N2 - A computational procedure has been developed which extends previous work on membrane wing aerodynamics to include the effects of viscosity in the fluid. The present membrane wing model is derived by combining an incremental, continuum based, finite element formulation of the elastic membrane problem with a control volume formulation of the Navier-Stokes equations written in general curvilinear body-fitted coordinates. The model yields solutions for membrane shape, membrane stress, and the surrounding viscous flow field variables simultaneously. The results of the viscous flow based model are qualitatively in agreement with flow visualization studies reported in the literature. The effect of viscosity in the fluid leads to substantially different membrane surface pressures compared with the surface pressures predicted by an inviscid flow model.

AB - A computational procedure has been developed which extends previous work on membrane wing aerodynamics to include the effects of viscosity in the fluid. The present membrane wing model is derived by combining an incremental, continuum based, finite element formulation of the elastic membrane problem with a control volume formulation of the Navier-Stokes equations written in general curvilinear body-fitted coordinates. The model yields solutions for membrane shape, membrane stress, and the surrounding viscous flow field variables simultaneously. The results of the viscous flow based model are qualitatively in agreement with flow visualization studies reported in the literature. The effect of viscosity in the fluid leads to substantially different membrane surface pressures compared with the surface pressures predicted by an inviscid flow model.

UR - https://openalex.org/W2943970975

UR - https://www.scopus.com/pages/publications/85006493425

U2 - 10.2514/6.1993-2955

DO - 10.2514/6.1993-2955

M3 - Conference Paper

T2 - AIAA 23rd Fluid Dynamics, Plasmadynamics, and Lasers Conference, 1993

Y2 - 6 July 1993 through 9 July 1993

ER -

A viscous flow based membrane wing model

Abstract

Conference

Bibliographical note

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