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. You can vary the angle of attack ( ... ) of the uniform onset flow with the airfoil. A panel method using straightline vortex panels of linearly varying strength and external Neumann boundary conditions provide the potential-flow solution. The default graphic is a plot of the surface pressure coefficient. The plot includes values for the lift coefficient ( ... ), pitching moment coefficient about the leading edge ( ... ), and location of the center of pressure ( ... ). The yellow dot on the graph shows the location of the center of pressure. Alternatively, you can chose to display a flow visualization graphic showing a stream plot of the velocity field. This is an important check on the plausibility of the potential-flow solution. This Demonstration is a companion to the Demonstration "Potential Flow over a NACA Four Digit Airfoil", where the airfoil geometry is specified by algebraic equations.

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