![]() 0 to 90% Thickness (%) 12 Third & fourth digit. 0 to 9% Max camber position (%) 40 Second digit. (set) Search Dat file Applications Airfoil database search My airfoils Airfoil plotter Airfoil comparison Reynolds number calc NACA 4 digit generator NACA 5 digit generator Information Airfoil data Lift/drag polars Generated airfoil shapes Searches Symmetrical airfoils NACA 4 digit airfoils NACA 5 digit airfoils NACA 6 series airfoils Airfoils A to Z A a18 to avistar (88) B b29root to bw3 (22) C c141a to curtisc72 (40) D dae11 to du861372 (28) E e1098 to esa40 (209) F falcon to fxs21158 (121) G geminism to gu255118 (419) H hh02 to ht23 (63) I isa571 to isa962 (4) J j5012 to joukowsk0021 (7) K k1 to kenmar (11) L l1003 to lwk80150k25 (24) M m1 to mue139 (95) N n0009sm to nplx (174) O oa206 to oaf139 (9) P p51droot to pw98mod (16) R r1046 to rhodesg36 (63) S s1010 to supermarine371ii (176) T tempest1 to tsagi8 (8) U ua2 to usnps4 (36) V v13006 to vr9 (17) W waspsm to whitcomb (4) Y ys900 to ys930 (3) List of all airfoils Site Home Contact Privacy Policy NACA 4 digit airfoil generator (NACA 2412 AIRFOIL) Max Camber (%) 2 First digit. The airfoil is described using six digits in the following sequence:įor example, the NACA 61 2-315 a=0.5 has the area of minimum pressure 10% of the chord back, maintains low drag 0.2 above and below the lift coefficient of 0.3, has a maximum thickness of 15% of the chord, and maintains laminar flow over 50% of the chord.įurther advancement in maximizing laminar flow achieved by separately identifying the low pressure zones on upper and lower surfaces of the airfoil.Airfoil Tools Search 1638 airfoils Tweet Thích 1,5K You have 0 airfoils loaded. Two 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.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 formula for the shape of a NACA 00xx foil, with "xx" being replaced by the percentage of thickness to chord, is: y t = 5 t c, Plot of a NACA 0015 foil, generated from formula The 15 indicates that the airfoil has a 15% thickness to chord length ratio: it is 15% as thick as it is long.Įquation for a symmetrical 4-digit NACA airfoil The NACA 0015 airfoil is symmetrical, the 00 indicating that it has no camber. Four-digit series airfoils by default have maximum thickness at 30% of the chord (0.3 chords) from the leading edge. The NACA four-digit wing sections define the profile by: 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. 1.2 The equation for a cambered 4-digit NACA airfoil.1.1 Equation for a symmetrical 4-digit NACA airfoil.
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