![]() ![]() Note that in this equation, at (x/c) = 1 (the trailing edge of the airfoil), the thickness is not quite zero. t is the maximum thickness as a fraction of the chord (so 100 t gives the last two digits in the NACA 4-digit denomination).y is the half thickness at a given value of x (centerline to surface), and.x is the position along the chord from 0 to c,.The formula for the shape of a NACA 00xx foil, with "xx" being replaced by the percentage of thickness to chord, is: Plot of a NACA 0015 foil, generated from formula Equation for a symmetrical 4-digit NACA airfoil 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. Four-digit series airfoils by default have maximum thickness at 30% of the chord (0.3 chords) from the leading edge. 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.One digit describing the distance of maximum camber from the airfoil leading edge in tens of percent's of the chord.One digit describing maximum camber as percentage of the chord.The NACA four-digit wing sections define the profile by: 1.2 Equation for a cambered 4-digit NACA airfoil.1.1 Equation for a symmetrical 4-digit NACA airfoil.
0 Comments
Leave a Reply. |
AuthorWrite something about yourself. No need to be fancy, just an overview. ArchivesCategories |