11/5/2022 0 Comments Naca supersonic airfoil generatorTwo digits describing the maximum thickness in percent of chord.įor example, the NACA 16-123 airfoil has minimum pressure 60% of the chord back with a lift coefficient of 0.1 and maximum thickness of 23% of the chord.Īn improvement over 1-series airfoils with emphasis on maximizing laminar flow.One digit describing the lift coefficient in tenths.One digit describing the distance of the minimum pressure area in tens of percent of chord.The 1-series airfoils are described by five digits in the following sequence: Prior to this, airfoil shapes were first created and then had their characteristics measured in a wind tunnel. In addition, for a more precise description of the airfoil all numbers can be presented as decimals.Ī new approach to airfoil design pioneered in the 1930s in which the airfoil shape was mathematically derived from the desired lift characteristics. One digit describing the distance of maximum thickness from the leading edge in tens of percent of the chord.įor example, the NACA 1234-05 is a NACA 1234 airfoil with a sharp leading edge and maximum thickness 50% of the chord (0.5 chords) from the leading edge.One digit describing the roundness of the leading edge with 0 being sharp, 6 being the same as the original airfoil, and larger values indicating a more rounded leading edge. #NACA SUPERSONIC AIRFOIL GENERATOR CODE#The following table presents the various camber line profile coefficients:įour- and five-digit series airfoils can be modified with a two-digit code preceded by a hyphen in the following sequence: The third digit indicates a non-reflexed (0) or reflexed (1) trailing edge. The second digit is twice the longitudinal location of the maximum camber location (in 10ths). The first digit is 2/3 of the design lift coefficient (in 10ths). For a 230 camber-line profile (the first 3 numbers in the 5 digit series), is used.Ĭamber line profiles 3 digit camber lines ģ digit camber lines provide a very far forward location for the maximum camber. Finally, constant is determined to give the desired lift coefficient. The constant is chosen so that the maximum camber occurs at for example, for the 230 camber-line, and. Where the chordwise location and the ordinate have been normalized by the chord. The camber-line is defined in two sections: The NACA five-digit series describes more complex airfoil shapes: 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).
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