An Analysis of Supersonic Flow in the Region of the Leading Edge of Curved Airfoils, Including Charts for Determining Surface-Pressure Gradient and Shock-Wave Curvature

Author:	Kraus, Samuel
Year:	1952
Document Type:	N/A
Series:	NACA Technical Notes
Report Number:	NACA-TN-2729
Link:	https://digital.library.unt.edu/ark:/67531/metadc56161/