Investigation of Impulse-type Supersonic Compressor with Hub-tip Ratio of 0.6 and Turning to Axial Direction I : Performance of Rotor Alone
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Wilcox, Ward W↗
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Experimental investigation of a 0.4 hub-tip diameter ratio axial-flow compressor inlet stage at transonic inlet relative Mach numbers II : stage and blade-element performance
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Montgomery, John C↗
High-speed Cascade Tests of a Blade Section Designed for Typical Hub Conditions of High-flow Transonic Rotors
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Savage, Melvyn↗
Investigation of Impulse-type Supersonic Compressor with Hub-tip Ratio of 0.6 and Turning to Axial Direction II : Stage Performance with Three Different Sets of Stators
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Wilcox, Ward W↗
Experimental investigation of a 0.4 hub-tip diameter ratio axial-flow compressor inlet stage at transonic inlet relative Mach numbers III : effect of tip taper on over-all and blade-element performances
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Montgomery, John C↗
Experimental and Theoretical Investigation of Rotating-stall Characteristics of Single-stage Axial-flow Compressor with Hub-tip Ratio of 0.76
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Graham, Robert W↗
Experimental Investigation of a Transonic Axial-flow-compressor Rotor Designed for Sonic Inlet Velocity with an Inlet Hub-tip Radius Ratio of 0.35
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Boxer, Emanuel↗
Investigation of a 0.6 hub-tip radius-ratio transonic turbine designed for secondary-flow study I : design and experimental performance of standard turbine
Detailed design information including overall performance parameters, velocity diagrams, and blade surface velocities is presented. Experimental performance includes maps based on rating as well as total-pressure ratios showing the effect of exit whirl. Also included are results of surveys at the stator exit and downstream of the rotor at design speed and specific work. This information will be used as a standard for comparison with subsequent secondary-flow work.
Rohlik, Harold E↗
Experimental investigation of a 0.4 hub-tip diameter ratio axial-flow compressor inlet stage at transonic inlet relative Mach numbers IV : performance of tapered-tip rotor configuration with reset blade angles
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Montgomery, John C↗
Design and Investigation of a Transonic Axial-flow Compressor Rotor with an Inlet Hub-tip Radius Ratio of Essentially Zero
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Westphal, Willard R↗
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 sta
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Rohlik, Harold E↗
Investigation of a 0.6 Hub-tip Radius-ratio Transonic Turbine Designed for Secondary-flow Study II : Design and Experimental Performance of Turbine with Low-velocity-turning Stator and Standard Rotor
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Rohlik, Harold E↗
Two-dimensional Cascade Tests of NACA 65-(c(sub Zeta)(sub O))a(sub 10))10 Blade Sections at Typical Compressor Hub Conditions for Speeds up to Choking
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Emery, James C↗
Investigation of a High-flow Transonic-compressor Inlet Stage Having a Hub-tip Radius Ratio of 0.35
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Felix, A Richard↗
Investigation of a 0.6 Hub-tip Radius-ratio Transonic Turbine Designed for Secondary-flow Study IV : Rotor Loss Patterns as Determined by Hot-wire Anemometers with Rotor Operating in a Circumferentially Uniform Inlet Flow Field
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Kofskey, Milton G↗
Experimental performance of a 0.35 hub-tip radius ratio transonic axial-flow-compressor stage designed for 40 pounds per second per unit frontal area
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Cullom, Richard R↗
Transonic Investigation of an Axial-flow Compressor Rotor with a Hub-tip Ratio of 0.75 and Blades Having NACA A(sub 2)i(sub 8b) Mean Lines
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Bernot, Peter T↗
Hub-mounted actuators for blade pitch collective control
Blade collective pitch control is provided for a rotor system by rotary actuators located between adjacent blades. Each actuator is connected to the leading edge of one adjacent blade and the trailing edge of the other adjacent blade.
Jeffery, Philip A. E.↗