Computational Analysis Of Incompressible Viscous Flow Over Single And Multi-Element Airfoils
The flow-field around a multi-element airfoil with leading-edge slat and trailing-edge flap in landing configuration was performed as well as the prediction of the time dependent flow over a NACA 0012 airfoil. The two dimensional incompressible Navier-Stokes equations with a numerical method bas...
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| Main Author: | |
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| Format: | Thesis |
| Language: | English English |
| Published: |
2003
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| Online Access: | http://psasir.upm.edu.my/id/eprint/12152/1/FK_2003_11.pdf http://psasir.upm.edu.my/id/eprint/12152/ |
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| Institution: | Universiti Putra Malaysia |
| Language: | English English |
| Summary: | The flow-field around a multi-element airfoil with leading-edge slat and
trailing-edge flap in landing configuration was performed as well as the prediction of
the time dependent flow over a NACA 0012 airfoil.
The two dimensional incompressible Navier-Stokes equations with a
numerical method based on the pseudo-compressibility approach was developed to
simulate viscous turbulent flow around single and multi-element airfoils. The
algorithm uses upwind-biased scheme of third order accuracy for the calculation of
the inviscid fluxes, while a second order central differencing is used for viscous
fluxes, the equations are solved using Lower-Upper Symmetric Gauss Seidel (LUSGS)
scheme. The grids around multi-element airfoil are efficiently generated using
a multi-block structure technique.The Baldwin-Lomax algebraic turbulence model is used to consider the effect
of turbulence. Computed results for the studied cases were compared with
experimental data in terms of surface pressure and lift coefficients which show
reasonable agreement.
Key Words: Multi-Element Airfoil, Pseudo-Compressibility, Confluent Boundary
Layer, Flow Separation, Baldwin-Lomax Turbulence Model |
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