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National Advisory Committee for Aeronautics Collection
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National Advisory Committee for Aeronautics Collection
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Investigation of two-stage air-cooled turbine suitable for flight at Mach number of 2.5 1: Velocity-diagram study
Investigation of Two-Stage Counterrotating Compressor. 3: Design of Second-Stage Rotor and Preliminary Over-All Performance
Performance of a Double-Ramp Side Inlet With Combinations of Fuselage, Ramp, and Throat Boundary-Layer Removal, Mach Number Range, 1.5 to 2.0
The change with mass-flow ratio of the cowl pressure drag of normal-shock inlets at supersonic speeds
Effect of fuels on screaming in 200-pound-thrust liquid-oxygen - fuel rocket engine
Fabrication Techniques and Heat-Transfer Results for Cast-Cored Air-Cooled Turbine Blades
Free-flight measurements of the zero-lift drag of several wings at Mach numbers from 1.4 to 3.8
Investigation of the Use of Area Suction to Increase the Effectiveness of Trailing-Edge Flaps of Various Spans on a Wing of 45 Degree Sweepback and Aspect Ratio 6
Effect of Inlet-Guide-Vane Angle on Blade Vibration and Rotating Stall of 13-Stage Axial-Flow Compressor in Turbojet Engine
Effect of Inlet-Guide-Vane Angle on Performance Characteristics of a 13-Stage Axial-Flow Compressor in a Turbojet Engine
Gas-turbine-engine performance when heat from liquid-cooled turbines is rejected ahead of, within, or behind main compressor
Investigation of two-stage counterrotating compressor I : design and over-all performance of transonic first compressor stage
A Simplified Method for Approximating the Transient Motion in Angles of Attack and Sideslip During a Constant Rolling Maneuver
Temperatures in a J47-25 turbojet-engine turbine section during steady-state and transient operation in an altitude test stand
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