Examples of airfoil

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The obstacle will be referred to either as an airfoil or as a wing.
The probes are supported by a streamline section in the form of a symmetric airfoil.
The two-dimensional sail is considered in a free-streamline model to complement the oft-considered airfoil model which is limited to small angles of attack.
The inhomogeneous term is the contribution due to the disturbances created by the moving airfoil ahead of the shock.
The resulting lift coefficients which are plotted in figure 6 do not agree with those predicted by the airfoil analysis.
The disparity is embedded in the assumption that there is not separation in the airfoil theory while there is separation in the present case.
This is as might be expected physically, presumably foretelling the onset of a higher mode as predicted by the airfoil model.
Their downstream motion being decelerated recognizably, they stay longer in the vicinity of the oscillating airfoil.
Global interaction of the boundary layer separating from an obstacle with resulting open/closed wakes is studied for a thin airfoil in a steady flow.
The visual field of the camera is about 3 to 4 chords in width and 2-3 chords in height inclusive of the airfoil itself.
Examples include heart valve leaflets, parachute canopies, thin airfoils (including bird, insect, or bat wings), sails, kites, flags, and weather vanes.
For example, when performing airfoil or aircraft calculations, the functionals of interest are almost always surface integrals.
The starting flows past a two-dimensional oscillating and translating airfoil are investigated by visualization experiments and numerical calculations.
The probes were attached to an airfoil-shaped strut connected t o a traversing mechanism through sealed slots in the tunnel side wall.
This electrode is a ringstyle thin film of the metal attached onto the airfoil surface.
It was confounded by the tendency for a separation cavity to form on the upper surface of the airfoil towards the trailing edge.
A few examples are transonic airfoils, supersonic air intakes, propelling nozzles at non-adapted configuration, and deflected control surfaces of vehicles at transonic or supersonic speed.
This leads, in most cases, to generation of keen noises and marked vibrations of the airfoil body.
This model complements rather than supercedes the airfoil model because of different ranges of validity in the angle of attack.

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