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. (Author)
Flight Test Investigation of Transonic Shock-Boundary Layer Phenomena, Volume 1
1968
75 pages
Report
No indication
English
Aerodynamics , Jet transport planes , Sweptback wings , Boundary layer transition , Flight testing , Shock waves , Transonic wind tunnels , Wind tunnel models , Laminar boundary layer , Turbulent boundary layer , Interactions , Pitot tubes , Aerodynamic characteristics , Aerodynamic loading , Flow separation , Reynolds number , Angle of attack , Wing body configurations , Transonic airfoils , Shock(Mechanics) , Laminar flow control , C-141 aircraft , Graphs(Charts)
Analytic investigation of transonic shock-boundary layer interaction
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