Military aircraft airfoil database4/29/2024 The 15 indicates that the airfoil has a 15% thickness to chord length ratio: it is 15% as thick as it is long. The NACA 0015 airfoil is symmetrical, the 00 indicating that it has no camber. įor example, the NACA 2412 airfoil has a maximum camber of 2% located 40% (0.4 chords) from the leading edge with a maximum thickness of 12% of the chord. Last two digits describing maximum thickness of the airfoil as percent of the chord.Second digit describing the distance of maximum camber from the airfoil leading edge in tenths of the chord.First digit describing maximum camber as percentage of the chord.This list is titled as Incomplete, as there are many aircraft. The NACA four-digit wing sections define the profile by: Many of the airfoils listed below can be found at the companion site: UIUC Airfoil Data Site. These figures and shapes transmitted the sort of information to engineers that allowed them to select specific airfoils for desired performance characteristics of specific aircraft. Engineers could quickly see the peculiarities of each airfoil shape, and the numerical designator ("NACA 2415," for instance) specified camber lines, maximum thickness, and special nose features. By 1929, Langley had developed this system to the point where the numbering system was complemented by an airfoil cross-section, and the complete catalog of 78 airfoils appeared in the NACA's annual report for 1933. According to the NASA website:ĭuring the late 1920s and into the 1930s, the NACA developed a series of thoroughly tested airfoils and devised a numerical designation for each airfoil - a four digit number that represented the airfoil section's critical geometric properties. NACA initially developed the numbered airfoil system which was further refined by the United States Air Force at Langley Research Center. Demonstration of the method is shown for 2D airfoil and 3D fighter. The NACA airfoil series is a set of standardized airfoil shapes developed by this agency, which became widely used in the design of aircraft wings. Combination of space mapping and variable fidelity modeling is presented in this paper. It played a crucial role in advancing aviation technology, including the development of airfoils, which are the cross-sectional shapes of wings and other aerodynamic surfaces. federal agency founded in 1915 to undertake, promote, and institutionalize aeronautical research. NACA stands for the National Advisory Committee for Aeronautics, which was a U.S. thickness 5: Camber 6: Upper surface 7: Trailing edge 8: Camber mean-line 9: Lower surface Profile lines – 1: Chord, 2: Camber, 3: Length, 4: Midline A: blue line = chord, green line = camber mean-line, B: leading-edge radius, C: xy coordinates for the profile geometry (chord = x axis y axis line on that leading edge) The UIUC Airfoil Coordinates Database includes the airfoils. In the case of variable sweep, Langley engineers came up with the. Airfoil Data Site is a collection of airfoil coordinates and airfoil related links. Wing shape Profile geometry – 1: Zero-lift line 2: Leading edge 3: Nose circle 4: Max. It was adopted by the Air Force for the F-111 and the B-1 bomber and the F-14 for the Navy.
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