Abstract:
An approximate method for designing a three-element airfoil by a given velocity distribution on its surface as a function of the arc abscissa is formulated. The main point of the method is the reduction of a triply-connected flow region to a simply-connected one, located on a many-sheeted Riemann surface, by inserting flow suction and blowing channels, asymptotically tending to circular, between the airfoil elements. Examples of design calculations are presented.
Keywords:inverse boundary-value problem of aerodynamics, three-element airfoil, flap, slat.
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