The effectiveness at high subsonic Mach numbers of a 20-percent-chord plain trailing-edge flap on the NACA 65-210 airfoil section

Louis S. Stivers, Jr.
naca-tn-3127
Mar 1954


An analysis has been made of the effectiveness of a 20-percent-chord plain trailing-edge flap on the NACA 65-210 airfoil section from section lift-coefficient data obtained at Mach numbers from 0.30 to 0.875. The analysis also includes a comparison of the effectiveness of this flap with that of a spoiler and a dive-recovery flap on the same airfoil section.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1954/naca-tn-3127.pdf