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Altitude Starting Tests of a 1000-Pound-Thrust Solid-Propellant Rocket

Description: Four solid-propellant rocket engines of nominal 1000-pound-thrust were tested for starting characteristics at pressure altitudes ranging from 112,500 to 123,000 feet and at a temperature of -75 F. All engines ignited and operated successfully. Average chamber pressures ranged from 1060 to ll90 pounds per square inch absolute with action times from 1.51 to 1.64 seconds and ignition delays from 0.070 t o approximately 0.088 second. The chamber pressures and action times were near the specifications, but the ignition delay was almost twice the specified value of 0.040 second.
Date: September 13, 1957
Creator: Sloop, John L.; Rollbuhler, R. James & Krawczonek, Eugene M.
Partner: UNT Libraries Government Documents Department

Investigation of a 0.6 Hub-tip Radius-ratio Transonic Turbine Designed for Secondary-flow Study. Iii - Experimental Performance With Two Stator Configurations Designed to Eliminate Blade Wakes and Secondary-flow Effects and Conclusions From Entire Stator Investigation

Description: Hub-tip radius ratio transonic turbine for secondary flow - stator configurations designed to eliminate blade wakes and secondary-flow effects.
Date: September 17, 1957
Creator: Moffitt, T. P.; Rohlik, H. E. & Wintucky, W. T.
Partner: UNT Libraries Government Documents Department

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