Possible application of blade boundary-layer control to improvement of design and off-design performance of axial-flow turbomachines
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BOUNDARY LAYER CONTROL - COMPRESSORS↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Design and performance of experimental axial-discharge mixed-flow compressor I : impeller design theory
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Goldstein, Arthur W↗
Design and experimental performance of a 0.35 hub-tip radius ratio transonic axial-flow-compressor rotor designed for 40 pounds per second per unit frontal area
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Montgomery, John C↗
Design and Test of Mixed-flow Impellers I : Aerodynamic Design Procedure
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Osborn, Walter M↗
Preliminary Investigation of Several Root Designs for Cermet Turbine Blades in Turbojet Engine II : Root Design Alterations
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Meyer, A J , Jr↗
Experimental Investigation of a 0.4 Hub-tip Diameter Ratio Axial-flow Compressor Inlet Stage at Transonic Inlet Relative Mach Numbers I : Rotor Design and Over-all Performance at Tip Speeds from 60 to 100 Percent of Design
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Serovy, George K↗
Analysis of factors affecting selection and design of air-cooled single-stage turbines for turbojet engines III : engine design-point performance
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Rossbach, Richard J↗
Investigation of Rotating Components of Counterrotating Two-spool Engines I : Analytical Investigation of Off-design Performance of Turbine Component Designed with and Without Outer-turbine Stator
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Steward, Warner L↗
Investigation of a High-performance Axial-flow Compressor Transonic Inlet Rotor Designed for 37.5 Pounds Per Second Per Square Foot of Frontal Area : Aerodynamic Design and Overall Performance
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Savage, Melvyn↗
Turboprop-engine design considerations II : design requirements and performance of turboprop engines with a single-spool high-pressure-ratio compressor
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Davison, Elmer H↗
A Transonic Investigation of Changing Indentation Design Mach Number on the Aerodynamic Characteristics of a 45 Degree Sweptback-wing--body Combination Designed for High Performance
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Loving, Donald L↗
Performance of variable two-dimensional inlet designed for engine-inlet matching I : performance at design Mach number of 3.07
The inlet was investigated with both a two-oblique-shock and an isentropic compression ramp. Provisions for a variety of bypass systems were incorporated and none decreased pressure recovery by more than about 1 percent. By utilizing throat boundary-layer control, critical pressure recoveries of 64 and 70 percent were obtained with the two-shock and isentropic ramps, respectively. Diffuser-exit air distortion was about 5 percent at critical operation Theoretical cowl pressure drag was equal to about 10 percent of the net thrust of an assumed engine.
Beheim, M A↗
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↗
Design and Test of Mixed-flow Impellers V : Design Procedure and Performance Results for Two Vaned Diffusers Tested with Impeller Model MFI-1B
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Hamrick, Joseph T↗
Investigation of a High-temperature Single-stage Turbine Suitable for Air Cooling and Turbine Stator Adjustment I : Design of Vortex Turbine and Performance with Stator at Design Setting
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Heaton, Thomas R↗
Relations between ship design and seaplane design
This report examines various aspects of seaplane construction; namely, stability, propulsion, water-tight bulkheads, fire protection, and construction.
Schnadel, Georg↗
Mars Sample Return, a concept point design by Team-X (JPL's Advanced Project Design Team)
A Mars sample return mission will answer critical questions concerning the possibility of life on Mars.
Mars Sample Return lander Orbiter autonomous landi↗