Lift and pitching-moment characteristics of an NACA 0006 airfoil are presented for various deflections of a 0.15-chord leading-edge flap and a 0.30-chord plain trailing-edge flap. Pressure-distribution data are presented in tabular form. The data were obtained at a Mach number of 0.15 and a Reynolds number of 4,500,000.
Section Characteristics of the NACA 0006 Airfoil with Leading-edge and Trailing-edge Flaps
1956-12-01
Miscellaneous
No indication
English
Section characteristics of NACA 0006 airfoil with area suction near leading edge
Engineering Index Backfile | 1954
|Unsteady Airfoil with Dynamic Leading- and Trailing-Edge Flaps
Online Contents | 2009
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