Some Effects of Aeroelasticity at Mach Numbers From 0.7 to 1.6 on the Rolling Effectiveness of Thin Flat-Plate Delta Wings Having 45 Degree Swept Leading Edges and Full-Span Constant-Chord Ailerons

Author:	Marley, Edward T.
Year:	1952
Document Type:	N/A
Series:	NACA Research Memorandums
Report Number:	NACA-RM-L51L05
Link:	https://digital.library.unt.edu/ark:/67531/metadc59891/