Accession Number:

ADA379807

Title:

Flow Characteristics Over a Lifting Wedge of Finite Aspect Ratio with Attached and Detached Chock Waves at a Mach Number of 1.40

Descriptive Note:

Technical note

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC

Personal Author(s):

• Hilton, John H., Jr

Report Date:

1952-06-01

Pagination or Media Count:

23.0

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.

Descriptors:

• *FLOW FIELDS
• *SUPERSONIC FLOW
• SHOCK WAVES
• ANGLE OF ATTACK
• WIND TUNNEL TESTS
• MACH NUMBER
• PRESSURE DISTRIBUTION
• ASPECT RATIO
• SCHLIEREN PHOTOGRAPHY

Subject Categories:

• Aerodynamics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE