Flow Characteristics Over a Lifting Wedge of Finite Aspect Ratio with Attached and Detached Chock Waves at a Mach Number of 1.40
Abstract
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1952
- Accession Number
- ADA379807
Entities
People
- John H. Hilton Jr
Organizations
- National Aeronautics and Space Administration