Effect of fuselage and tail surfaces on low-speed yawing characteristics of a swept-wing model as determined in curved-flow test section of Langley stability tunnel

Author:	Bird, John D.
Additional Authors:	Jaquet, Byron M.
Year:	1951
Document Type:	N/A
Series:	NACA Technical Notes
Report Number:	NACA-TN-2483
Link:	https://digital.library.unt.edu/ark:/67531/metadc55717/