Investigation at Mach Number 1.62 of the Pressure Distribution Over a Rectangular Wing With Symmetrical Circular-Arc Section and 30-Percent-Chord Trailing-Edge Flap

Author:	Czarnecki, K. R.
Year:	1950
Document Type:	N/A
Series:	NACA Research Memorandums
Report Number:	NACA-RM-L9J05
Link:	https://digital.library.unt.edu/ark:/67531/metadc58335/