Effects of Mach number up to 0.34 and Reynolds number up to 8,000,000 on the maximum lift coefficient of a wing of NACA 66-series airfoil sections

Author:	Furlong, G. Chester.
Additional Authors:	Fitzpatrick, James E.
Year:	1950
Document Type:	TNNA
Issuing Agency:	National Advisory Committee for Aeronautics,
SUDOC:	Y 3.N 21/5:6/2251
Series:	National Advisory Committee for Aeronautics ;
Report Number:	no. 2251
Subjects:	Reynolds number
	Lift (Aerodynamics)
	Mach number
	Airplanes--Models--Wings
	Aerofoils
Link:	https://hdl.handle.net/2027/mdp.39015086494815