English

NACA 64_1-412 Airfoil Data

This image is part of a series that was created for an open textbook, Aerodynamics and Aircraft Performance . The textbook is available here . Preferred citation: Kindred Grey (2021). "NACA 64_1-412 Airfoil Data." CC BY 4.0 . Adapted from NACA. Public domain. Alternative text: (a) Lift curve slopes are shown for Reynolds numbers of 3.0, 6.0, and 9.0 times 10 to the 6. The curves are linear between angles of attack, alpha knot, of negative 14 and 14 degrees, with stall resulting in curves back towards 0 past these values and a y-intercept of 0.25. The lower end of the lines stop within the linear portion for all but the 6.0 times 10 ^6 case. An additional case at 6.0 times 10^6 is shown with standard roughness, which follows the same linear path until alpha knot of 10, after which it turns down slightly before the other cases. A final two cases are also shown with a 0.2 times c length flap deflected by 60 degrees, which results in the curve being shifted upward to a new y-intercept of approximately 1.6 c sub l, and the linear portion shifted to be between alpha knots of negative 16 and 6 to 12 degrees, for when standard roughness is or is not applied, respectively . The moment coeff

Sign in with your free account to read, download EPUBs or listen.