A theoretical investigation of a low-correction windtunnel wall configuration for airfoil testing
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 tow...
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| Language: | English |
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2010
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| Online Access: | http://hdl.handle.net/2429/21535 |
| Summary: | 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. === Applied Science, Faculty of === Mechanical Engineering, Department of === Unknown |
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