![]() ![]() Airfoil database search My airfoils Airfoil plotter Airfoil comparison Reynolds number calc NACA 4 digit generator NACA 5 digit generator Information. A compilation of early measurements at low Reynolds numbers can be found in the work of Carmichael (1981) and Selig et al. Problems associated with lateral-control devices, leading-edge air intakes, and interference are briefly discussed, together with aerodynamic problems of application. Details of airfoil (aerofoil)(s809-nr) NRELs S809 Airfoil NREL HAWT airfoil S809 primary 21.0 Re2.0E+6 Clmax(S)1.00. The unique aerodynamic behavior of airfoils at low (Rec) impacts the performance of UAVs or any other systems that operate at low Reynolds numbers, such as vertical axis wind turbines, and propellers. Available data on high-lift devices are presented. The report includes an analysis of the lift, drag, pitching-moment, and critical-speed characteristics of the airfoils, together with a discussion of the effects of surface conditions. Detail data necessary for the application of the airfoils to wing design are presented in supplementary figures placed at the end of the paper. The general methods used to derive the basic thickness forms for NACA 6 and 7-series airfoils together with their corresponding pressure distributions are presented. New data are presented that permit the rapid calculation of the approximate pressure distributions for the older NACA four-digit and five-digit airfoils by the same methods used for the NACA 6-series airfoils. The 15 indicates that the airfoil has a 15% thickness to chord length ratio: it is 15% as thick as it is long.Summary of Airfoil Data The historical development of NACA airfoils is briefly reviewed. 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.The NACA four-digit wing sections define the profile by: 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. 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. 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) Wing shape Profile geometry – 1: Zero-lift line 2: Leading edge 3: Nose circle 4: Max.
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