Effect of thickness, camber, and thickness distribution on airfoil characteristics at Mach numbers up to 1.0

Author:	Daley, Bernard N
Year:	1956
Document Type:	N/A
Series:	NACA Technical Notes
Report Number:	NACA-TN-3607
Link:	https://digital.library.unt.edu/ark:/67531/metadc57800/