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A theoretical investigation of a low-correction windtunnel wall configuration for airfoil testing Malek, Ahmed Fouad
Abstract
This thesis deals with anew approach to reduce wall corrections in high-lift airfoil testing, by employing symmetrically transversely slotted walls. The solid elements of the slotted wall are symmetrical airfoils at zero incidence, the spaces between the slats are nonuniform, increasing linearly towards the rear. This wall configuration provides flow conditions close to the free air test environment which leads to negligible or. small wall corrections. The theory uses the potential flow surface vortex-element method, with "Full Load" Kutta Conditions satisfied on the test airfoil and wall slats. This method is very well supported by physical evidence and it is simple to use. The surface velocities can be calculated directly and the aerodynamic lift and pitching moment are determined by numerical integration of the calculated pressure distributions around the airfoil contour. This method can be developed in order to include the flow in the plenum chambers in the analysis.
Item Metadata
Title |
A theoretical investigation of a low-correction windtunnel wall configuration for airfoil testing
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Creator | |
Publisher |
University of British Columbia
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Date Issued |
1979
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Description |
This thesis deals with anew approach to reduce wall corrections in high-lift airfoil testing, by employing symmetrically transversely slotted walls. The solid elements of the slotted wall are symmetrical airfoils at zero incidence, the spaces between the slats are nonuniform, increasing linearly towards the rear. This wall configuration provides flow conditions close to the free air test environment which leads to negligible or. small wall corrections. The theory uses the potential flow surface vortex-element method, with "Full Load" Kutta Conditions satisfied on the test airfoil and wall slats. This method is very well supported by physical evidence and it is simple to use. The surface velocities can be calculated directly and the aerodynamic lift and pitching moment are determined by numerical integration of the calculated pressure distributions around the airfoil contour. This method can be developed in order to include the flow in the plenum chambers in the analysis.
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Genre | |
Type | |
Language |
eng
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Date Available |
2010-03-05
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Provider |
Vancouver : University of British Columbia Library
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Rights |
For non-commercial purposes only, such as research, private study and education. Additional conditions apply, see Terms of Use https://open.library.ubc.ca/terms_of_use.
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DOI |
10.14288/1.0094626
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URI | |
Degree | |
Program | |
Affiliation | |
Degree Grantor |
University of British Columbia
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Campus | |
Scholarly Level |
Graduate
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Aggregated Source Repository |
DSpace
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Item Media
Item Citations and Data
Rights
For non-commercial purposes only, such as research, private study and education. Additional conditions apply, see Terms of Use https://open.library.ubc.ca/terms_of_use.