TT: the maximum thickness in percent of chord, as in a four-digit NACA airfoil code.įor example, the NACA 23112 profile describes an airfoil with design lift coefficient of 0.3 (0.15 × 2), the point of maximum camber located at 15% chord (5 × 3), reflex camber (1), and maximum thickness of 12% of chord length (12).Īn improvement over 1-series airfoils with emphasis on maximizing laminar flow.S: a single digit indicating whether the camber is simple (S = 0) or reflex (S = 1),.P: a single digit for the x coordinate of the point of maximum camber (max.L: a single digit representing the theoretical optimal lift coefficient at ideal angle of attack CLI = 0.15 L (this is not the same as the lift coefficient CL ),.The NACA five-digit series describes more complex airfoil shapes. 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. Last two digits describing maximum thickness of the airfoil as percent of the chord.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.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: For each coefficient distribution by the attack angle, corresponding relations are constructed and can be used in design calculations via SplineCloud API. This repository contains basic data on the NACA airfoils: profile coordinates and performance data, including lift coefficients, drag coefficients, and pitching moment coefficients for various Reynolds numbers. The parameters in the numerical code can be entered into equations to precisely generate the cross-section of the airfoil and calculate its properties. The shape of the NACA airfoils is described using a series of digits following the word "NACA". The NACA airfoils are airfoil shapes for aircraft wings developed by the National Advisory Committee for Aeronautics (NACA).
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