Free-flight tests at Mach numbers from 0.8 to 1.4 to determine the effect on zero-lift drag of increasing the leading-edge bluntness of a 45 degree sweptback wing having an NACA 65A009 airfoil

Author:	Pepper, William B., Jr.
Year:	1952
Document Type:	N/A
Series:	NACA Research Memorandums
Report Number:	NACA-RM-L52F30
Link:	https://digital.library.unt.edu/ark:/67531/metadc59329/