Flow characteristics over a lifting wedge of finite aspect ratio with attached and detached shock waves at a Mach number of 1.40

John H. Hilton, Jr.
naca-tn-2712
Jun 1952


A series of schlieren photographs and pressure distributions are presented which show the effects of transition from an attached to a detached shock at the leading edge of a finite-span 8.2 degree wedge as the angle of attack is increased. These data were obtained in the Langley 4- by 4-foot supersonic tunnel at a Mach number of 1.40.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1952/naca-tn-2712.pdf