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Transonic Wind-Tunnel Investigation of Static Longitudinal Stability and Control Characteristics and Drag of a 0.05-Scale Model of the Chance Vought XF8U-3 Airplane : TED No. NACA AD 3133

Description: A transonic wind-tunnel investigation was made in the Langley 8-foot transonic pressure tunnel at the request of the Bureau of Aeronautics, Department of the Navy, of the static longitudinal stability and control characteristics and drag of a 0.05-scale model of the Chance Vought XF8U-3 airplane at Mach numbers from 0.80 to 1.20 with an average Reynolds number of 2.6 x 10(exp 6). The investigation included effects of the addition of the ventral fins, extension and removal of the missiles, deflection of the speed brake, addition of a fuselage fairing near the wing leading edge, and longitudinal control effectiveness. The model was statically stable throughout most of the range of positive lift coefficients, but some loss in horizontal-tail effectiveness may be expected near zero lift and a Mach number of 1.0. Installation of the ventral fins Increased the longitudinal stability from 2 to percent at a small drag-coefficient penalty. The speed-brake drag increment decreased with increasing angle of attack, and trim changes of about 2deg at low angles of attack may be expected at supersonic speeds. The increase in subsonic drag coefficient caused by extension of the three missiles to firing position was more than three times as great as the increase in drag-coefficient rise at supersonic speeds.
Date: September 20, 1957
Creator: Pierpont, P. Kenneth
Partner: UNT Libraries Government Documents Department