a=1 is the default if no value is given.įor example, the NACA 612-315 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. "a=" followed by a decimal number describing the fraction of chord over which laminar flow is maintained.Two digits describing the maximum thickness as percent of chord.One digit describing the design lift coefficient in tenths. ![]() The subscript digit gives the range of lift coefficient in tenths above and below the design lift coefficient in which favorable pressure gradients exist on both surfaces.One digit describing the distance of the minimum pressure area in tenths of the chord.The airfoil is described using six digits in the following sequence: ![]()
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