FLIGHT TEST INVESTIGATION OF TRANSONIC SHOCK-BOUNDARY LAYER PHENOMENA. VOLUME II.
Final technical rept. 5 Oct 67-15 Jul 68,
LOCKHEED-GEORGIA CO MARIETTA
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A flight test investigation was made using a 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. The report contains a detailed discussion of the data acquisition and reduction procedures plus a complete presentation of the basic data. 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
- Transport Aircraft