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An airfoil (American English) or aerofoil (British English) is a streamlined body that is capable of generating significantly more lift than drag. [1] Wings, sails and propeller blades are examples of airfoils.
A supercritical aerofoil (supercritical airfoil in American English) is an airfoil designed primarily to delay the onset of wave drag in the transonic speed range. Supercritical airfoils are characterized by their flattened upper surface, highly cambered ("downward-curved") aft section, and larger leading-edge radius compared with NACA 6-series ...
The NACA four-digit wing sections define the profile by: [2] First digit describing maximum camber as percentage of the chord.; Second digit describing the distance of maximum camber from the airfoil leading edge in tenths of the chord.
A foil is a solid object with a shape such that when placed in a moving fluid at a suitable angle of attack the lift (force generated perpendicular to the fluid flow) is substantially larger than the drag (force generated parallel to the fluid flow).
Within the assumptions embodied in thin airfoil theory, the aerodynamic center is located at the quarter-chord (25% chord position) on a symmetric airfoil while it is close but not exactly equal to the quarter-chord point on a cambered airfoil.
Clark Y is the name of a particular airfoil profile, widely used in general purpose aircraft designs, and much studied in aerodynamics over the years. The profile was designed in 1922 by Virginius E. Clark using thickness distribution of the German-developed Goettingen 398 airfoil. [1]
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The KF airfoil was designed by Richard Kline and Floyd Fogleman. Aircraft wing showing the KFm4 Step. In the early 1960s, Richard Kline wanted to make a paper airplane that could handle strong winds, climb high, level off by itself and then enter a long downwards glide.