Transonic-wing investigation in the Langley 8-foot high-speed tunnel at high subsonic Mach numbers and at a Mach number of 1.2
Subtitle: analysis of pressure distribution of wing-fuselage configuration having a wing of 45 degrees sweepback, aspect ratio 4, taper ratio  0.6, and NACA 65A006 airfoil section
By: Donald L. Loving and Bruce B. Estabrooks.
Contributors: Estabrooks, Bruce B.; Langley Aeronautical Laboratory
Publisher: National Advisory Committee for Aeronautics
Published: 1951
Place of publication: Washington
Number of pages: 132
Subjects: Transonic flow; Wings
Notes: Bibliographical references: p.26-27.