Publisher's Synopsis
Excerpt from An Artificial Viscosity Method for the Design of Supercritical Airfoils
As the speed of the wing is increased, the supersonic zone grows in size and the pressure jump becomes larger. The occurrence of such shocks in the flow imposes a retarding force on the wing known as wave drag, which is one reason for the drag rise seen in Figure l. The large pressure gradients present in strong shocks can also induce separa tion of the boundary layer of air that adheres to the wing because of friction; separation results in a decrease in lift and more drag. The study of transonic flow is therefore important not only because transonic flow encompasses the most economical regime for aircraft opera tion, but because the deterioration of an aircraft's efficiency at higher speeds is due to transonic effects.
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