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Numerical computation of viscous flow about unconventional airfoil shapesA new two-dimensional computer code was developed to analyze the viscous flow around unconventional airfoils at various Mach numbers and angles of attack. The Navier-Stokes equations are solved using an implicit, upwind, finite-volume scheme. Both laminar and turbulent flows can be computed. A new nonequilibrium turbulence closure model was developed for computing turbulent flows. This two-layer eddy viscosity model was motivated by the success of the Johnson-King model in separated flow regions. The influence of history effects are described by an ordinary differential equation developed from the turbulent kinetic energy equation. The performance of the present code was evaluated by solving the flow around three airfoils using the Reynolds time-averaged Navier-Stokes equations. Excellent results were obtained for both attached and separated flows about the NACA 0012 airfoil, the RAE 2822 airfoil, and the Integrated Technology A 153W airfoil. Based on the comparison of the numerical solutions with the available experimental data, it is concluded that the present code in conjunction with the new nonequilibrium turbulence model gives excellent results.
Document ID
19910000706
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Ahmed, S. (Iowa State Univ. of Science and Technology Ames, IA, United States)
Tannehill, J. C. (Iowa State Univ. of Science and Technology Ames, IA, United States)
Date Acquired
September 6, 2013
Publication Date
October 1, 1990
Subject Category
Aerodynamics
Report/Patent Number
CFD-24
ISU-ERI-AMES-91-110
NASA-CR-187343
NAS 1.26:187343
Accession Number
91N10019
Funding Number(s)
CONTRACT_GRANT: NAG1-645
PROJECT: ERI PROJ. 1874
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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