Study is undertaken to determine effects of leading edge flap deflection and boundary layer control on maximum lift and longitudinal stability; lift, drag, and pitching moment are measured at Reynolds number of 8.2 million for various combinations; model conformed to that of F-100 aircraft.
Low-speed wind-tunnel investigation of blowing boundary-layer control on leading- and trailing-edge flaps of large-scale, low-aspect-ratio, 45° swept-wing airplane configuration
NASA -- Memo
National Aeronautics and Space Administration -- Memorandums ; Memo 1-23-59A
1959
25 pages
Report
English
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