Investigation of NACA 64,2-432 and 64,3-440 airfoil sections with boundary-layer control and an analytical study of their possible applications

Elmer A. Horton, Stanley Frank Racisz, Nicholas J. Paradiso
naca-tn-2405
Jul 1951


NACA 64-series airfoil sections of 32- and 40-percent-chord thickness ratio have been derived and an investigation was made to determine the effect of boundary-layer control by means of suction through a slot at 0.60 airfoil chord on the pressure distribution, lift, and drag characteristics of the NACA 64,2-432 and 64,3-440 airfoil sections.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1951/naca-tn-2405.pdf