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Flow Characteristics Over a Lifting Wedge of Finite Aspect Ratio with Attached and Detached Chock Waves at a Mach Number of 1.40
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC
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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 deg 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.
APPROVED FOR PUBLIC RELEASE