Fluids – Lecture 18
نویسنده
چکیده
This zero-circulation property of source sheets has severe consequences for flow representation. Any aerodynamic model consisting only of a freestream and superimposed source sheets will have Γ = 0, and hence L = 0 as well. Hence, lifting flows cannot be represented by source sheets alone. This limitation is illustrated if we use source panels to model a flow expected to produce lift, such as that on an airfoil at an angle of attack. Examination of the streamlines reveals that the rear dividing streamline leaves the airfoil off one surface as shown in the figure. The model also predicts an infinite velocity going around the sharp trailing edge.
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