Charts for estimating performance of high-performance helicopters
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Gessow, Alfred↗
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Supplementary charts for estimating performance of high-performance helicopters
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Gessow, Alfred↗
Effects of compressibility on rotor hovering performance and synthesized blade-section characteristics derived from measured rotor performance of blades having NACA 0015 airfoil tip sections
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Shivers, James P↗
Performance of J33 turbojet engine with shaft-power extraction I : over-all engine performance
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Nettles, J C↗
Performance of 24-inch supersonic axial-flow compressor in air II : performance of compressor rotor at equivalent tip speeds from 800 to 1765 feet per second
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Johnsen, Irving A↗
Design and Performance of Experimental Axial-discharge Mixed-flow Compressor II : Performance of Impeller
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Wilcox, Ward W↗
Investigation of the I-40 jet-propulsion engine in the Cleveland altitude wind tunnel III : analysis of turbine performance and effect of tail-pipe design on engine performance
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Krebs, Richard P↗
Calculations of the performance of a compression-ignition engine-compressor turbine combination II : performance of complete combination
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Mendelson, Alexander↗
Performance of Experimental Turbojet-engine Combustor I : Performance of a One-eighth Segment of an Experimental Turbojet-engine Combustor
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Hill, Francis U↗
Performance of 24-inch Supersonic Axial-flow Compressor in Air I : Performance of Compressor Rotor at Design Tip Speed of 1600 Feet Per Second
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Ritter, William K↗
Altitude-test-chamber Investigation of Performance of a 28-inch Ram-jet Engine I : Combustion and Operational Performance of Four Combustion-chamber Configurations
An altitude-test-chamber investigation of a 28-inch-diameter ram-jet engine at a simulated flight Mach number of approximately 2.0 for altitudes of 40,000 to 50,000 feet was conducted at the NACA Lewis laboratory. Three different flame holders, varying in the number and size of the annular gutters, in conjunction with several fuel-injection systems were investigated. The combustion efficiency for the flame-holder fuel-injection system that provided the best over-all operational fuel-air-ratio range (0.03 to 0.075) was over 0.9 at a fuel-air ratio of about 0.065 for the altitude range investigated.
MISSILES, SPECIFIC TYPES↗
Load-Range Performance of Turbine-Propeller Engine in Transonic Speed Range and Comparison with Load-Range Performance of Turbojet Engine
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Lubarsky, Bernard↗
Design and Performance of an Experimental Axial-discharge Mixed-flow Compressor II : Over-all Performance of Impeller and Supersonic-diffuser Combination
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Wilcox, Ward W↗
Free-flight Performance of 16-inch Diameter Supersonic Ram-jet Units IV : Performance of Ram-jet Units Designed for Combustion Chamber Inlet Mach Number of 0.21 at Free-stream Mach Number of 1.6 over a Range Flight Conditions
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Rabb, Leonard↗
Performance of J35-A-23 Compressor I : Over-all Performance Characteristics at Equivalent Speeds from 20 to 100 Percent of Design
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Medeiros, Arthur A↗
Altitude-test-chamber Investigation of Performance of a 28-inch Ram-jet Engine IV : Effect of Inlet-air Temperature, Combustion-chamber-inlet Mach Number, and Fuel Volatility on Combustion Performance
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Kahn, Robert W↗
Altitude-test-chamber investigation of performance of a 28-inch ram-jet engine III : combustion and operational performance of three flame holders with a center pilot burner
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Shillito, Thomas B↗
Investigation of Performance of Several Double-shroud Ejectors and Effect of Variable-area Exhaust Nozzle on Single Ejector Performance
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Ellis, C W↗