Accession Number:

AD0835774

Title:

Flight Test Investigation of Transonic Shock-Boundary Layer Phenomena, Volume 1

Descriptive Note:

[Technical Report, Final Report]

Corporate Author:

LOCKHEED-GEORGIA CO MARIETTA

Personal Author(s):

• Cahill, Jones F.
• Cooper, Bill L.

Report Date:

1968-07-01

Pagination or Media Count:

89

Abstract:

A flight test investigation was made using a Lockheed C-141 airplane to obtain data related to scale effects on transonic shock-boundary layer interactions. The primary measurements consisted of wing surface chordwise pressure distributions at three spanwise stations, and boundary layer profiles for three chordwise positions at one spanwise station. Volume I contains the data analysis and discussions of the test results. Results obtained, when compared with previously available wind tunnel data, showed that large scale effects on chordwise pressure distribution can occur with turbulent boundary layers on a wing having small Mach number gradients forward of the shock. A shock-induced separation, followed by flow reattachment, was shown to occur when the shock pressure rise reached a value approximately equal to that indicated in NACA Report 1356. For wing sections of the type used on the C-141, scale effects on buffet phenomena should be anticipated also.

Descriptors:

• pressure distribution
• aircrafts
• boundary layer
• data acquisition
• turbulent boundary layer
• acquisition
• leading edges
• pressure measurement
• mach number
• shock waves
• standards
• static pressure
• transonic flow
• wind tunnel tests
• wind tunnels
• abstracts
• boundaries

Subject Categories:

• AERODYNAMICS
• Transport Aircraft

Distribution Statement:

[A, Approved For Public Release]