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Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine 1 - Analysis of Turbine Performance

Description: A wind tunnel investigation was conducted to determine the performance of a turbine operating as an integral part of a turbojet engine. Data was obtained while the engine was running over full operable range of speeds at various altitudes and flight mach numbers, and with four nozzles of different outlet areas.A maximum turbine efficiency of 0.875 was obtained at altitude of 15 thousand feet, Mach number 0.53, and corrected turbine speed of 5900 rpm.
Date: August 23, 1948
Creator: Conrad, Earl W.; Dietz, Robert O., Jr. & Golladay, Richard L.
Item Type: Refine your search to only Report
open access

Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine 2 - Analysis of Compressor Performance

Description: Compressor performance properties for two 11-stage compressors of 3000-pound-thrust axial-flow turbojet engines were determined. Data are presented for a range of simulated altitudes and a range of Mach numbers for various modifications of the engine.
Date: August 23, 1948
Creator: Dietz, Robert O., Jr.; Berdysz, Joseph J. & Howard, Ephraim M.
Item Type: Refine your search to only Report
open access

Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine 3 - Analysis of Combustion-Chamber Performance

Description: Combustion chamber performance properties of a 3000-pound-thrust axial-flow turbojet engine were determined. Data are presented for a range of simulated altitudes from 15,000 to 45,0000 feet and a range of Mach numbers from 0.23 to 1.05 for various modifications of the engine.
Date: August 23, 1948
Creator: Campbell, Carl E.
Item Type: Refine your search to only Report
open access

Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, 4, Operational Characteristics

Description: An investigation was conducted to evaluate the operational characteristics of a 3000 pound thrust axial flow turbojet engine over a range of simulated altitudes from 2000 to 50,000 feet and simulated flight Mach numbers from 0 to 1.04 throughout the operable range of engine speeds. Engine operating range, acceleration, deceleration, starting, altitude, and flight Mach number compensation of the fuel control system, and operation of the lubrication system at high and low ambient air temperatures… more
Date: August 23, 1948
Creator: Hawkins, W. Kent & Meyer, Carl L.
Item Type: Refine your search to only Report
open access

Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, Part 5, Performance and Windmilling Drag Characteristics

Description: "An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the performance and windmilling drag characteristics of an original and a modified turbojet engine of the same type. Data have been obtained at simulated altitudes from 5000 to 45,000 feet, simulated flight Mach numbers from 0.09 to 1.08, and engine speeds from 4000 to 12,500 rpm. Engine performance data are presented for both engines to show the effects of altitude at a flight Mach number of 0.25 and of… more
Date: August 23, 1948
Creator: Meyer, Carl L. & Bloomer, Harry E.
Item Type: Refine your search to only Report
open access

Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine. 2 - Operational Characteristics

Description: From Summary: "An investigation was conducted in the Cleveland altitude wind tunnel to determine the operational characteristics of an axial flow-type turbojet engine with a 4000-pound-thrust rating over a range of pressure altitudes from 5,000 to 50,000 feet, ram pressure ratios from 1.00 to 1.86, and temperatures from 60 deg to -50 deg F. The low-flow (standard) compressor with which the engine was originally equipped was replaced by a high-flow compressor for part of the investigation. The e… more
Date: August 6, 1948
Creator: Fleming, William A.
Item Type: Refine your search to only Report
open access

Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine, 3, Performance Characteristics with the High-Flow Compressor

Description: A wind tunnel investigation was conducted to determine the performance of a 4000-pound-thrust axial-flow turbojet engine with a high flow compressor. Pressure altitudes included 5000 to 40000 feet with ram pressure ratios from 1.00 to 1.82. Altitudes included 20000 to 40000 feet and ram pressure ratios from 1.09 to 1.75. A comparison is made between engine performance with high flow and low flow compressors.
Date: August 5, 1948
Creator: Fleming, William A. & Golladay, Richard L.
Item Type: Refine your search to only Report
open access

Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine, 4 - Analysis of Compressor Performance

Description: Operating characteristics of the 11-stage 4000-pound-thrust axial-flow turbojet engine were determined. A standard compressor and a compressor with the blade angles of the rotor and stator blades increased 5 degrees to obtain greater air flow, were investigated.
Date: August 5, 1948
Creator: Dietz, Robert O., Jr. & Suozzi, Frank L.
Item Type: Refine your search to only Report
open access

Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine 5 - Analysis of Turbine Performance

Description: "Performance characteristics of the turbine of a 4000-pound-thrust axial-flow turbojet engine was determined in investigations of the complete engine in the NACA Cleveland altitude wind tunnel. Characteristics are presented as functions of the total-pressure ratio across the turbine and of turbine speed and gas flow corrected to sea-level conditions. Three turbine nozzles of different areas were used to determine the area that gave optimum performance" (p. 1).
Date: August 4, 1948
Creator: Krebs, Richard P. & Hensley, Reece V.
Item Type: Refine your search to only Report
open access

Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine 6: Combustion-Chamber Performance

Description: "An analysis of the performance of the types A, B, and C combustion chambers of the 4000-pound-thrust axial-flow turbojet engine is presented. The data were obtained from investigations of the complete engine over a range of pressure altitudes from 5000 to 40,000 feet and ram pressure ratios from 1.00 to 1.86. The combustion-chamber pressure losses, the effect of the losses on cycle efficiency, and the combustion efficiency are discussed" (p. 1).
Date: August 4, 1948
Creator: Pinkel, I. Irving & Shames, Harold
Item Type: Refine your search to only Report
open access

Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine, Part 1, Performance and Windmilling Drag Characteristics

Description: From Summary: "The results of altitude-wind-tunnel tests conducted to determine the performance of an axial-flow-type 4000-pound-thrust turbojet engine for a range of pressure altitudes from 5000 to 40,000 feet and ram pressure ratios from 1.02 to 1.86 are presented and the experimental and analytical methods employed are discussed. By means of suitable generalizing factors applied to the measured performance data, curves were obtained from which the engine performance at any altitude for a giv… more
Date: August 3, 1948
Creator: Fleming, William A.
Item Type: Refine your search to only Report
open access

Analysis of parameters for thrust control of a turbojet engine equipped with air-inlet throttle and variable-area exhaust nozzle

Description: From Introduction: "In this report, altitude, airplane velocity, exhaust-nozzle area, and turbine-inlet temperature were chosen and corresponding engine speed, fuel flow, and throttle pressure ratio were found. A detailed discussion of the engine analysis and the calculations used are presented in Appendix A. The derivations of the principal equations used are presented in appendix B."
Date: August 10, 1948
Creator: Boksenbom, Aaron S. & Feder, Melvin S.
Item Type: Refine your search to only Report
open access

Analysis of planing data for use in predicting hydrodynamic impact loads

Description: From Introduction: "The magnitude of hydrodynamic loads experienced by seaplanes during a landing impact has been investigated experimentally and theoretically by the National Advisory Committee for Aeronautics. The results as reported in references 1 and 2 provide a rational means of determining loads on conventional V-bottom hulls in a step landing."
Date: August 1948
Creator: Steiner, Margaret F.
Item Type: Refine your search to only Report
open access

Analytical investigation of effect of water-cooled turbine blades on performance of turbine-propeller power plants

Description: "Finally the work of the report is applied exclusively to consideration of the turbine-propeller power plant because previous performance analyses of the various gas-turbine propulsion systems combine with recent improvements in propeller design indicate that it is this combination which, will give the best over-all performance in the speed ranges considered" (p. 5).
Date: August 16, 1948
Creator: Bowman, William D
Item Type: Refine your search to only Report
open access

Application of one part of Von Karman's two-dimensional transonic similarity law to drag data of NACA 65-series wings

Description: Report presenting the use of Von Karman's two-dimensional transonic similarity law as applied to drag data of three different thickness wings with NACA 65-series sections and aspect ratios of 7.6 over a range of Mach numbers. The correlation was found to be satisfactory, with results better in the subsonic range than in the supersonic range.
Date: August 24, 1948
Creator: Amer, Kenneth B.
Item Type: Refine your search to only Report
open access

Appreciation and Prediction of Flying Qualities

Description: Note presenting a summary of some results of recent research that will aid the designers of an airplane in selecting or modifying a configuration to provide satisfactory stability and control characteristics. A discussion is given of the reasons for the requirements, of the factors involved in obtaining satisfactory flying qualities, and of the methods used in predicting the stability and control characteristics of the airplane.
Date: August 1948
Creator: Phillips, William Hewitt
Item Type: Refine your search to only Report
open access

Axial fatigue tests at zero mean stress of 24S-T and 75S-T aluminum-alloy strips with a central circular hole

Description: From Summary: "Axial fatigue tests at zero mean stress have been made on 0.032- and 0.064-inch 24S-T and 0.032-inch 75S-T sheet-metal specimens 1/4, 1/2, 1, and 2 inches wide without a hole and with central holes giving a range of hole diameter D to specimen width W from 0.01 to 0.95. No systematic difference was noted between the results for the 0.032-inch and the 0.064-inch specimens although the latter seemed the more consistent. In general the fatigue strength based on the minimum section d… more
Date: August 1948
Creator: Brueggeman, W. C. & Mayer, M., Jr.
Item Type: Refine your search to only Report
open access

Bearing strength of some aluminum-alloy sand castings

Description: Report presenting bearing tests made of aluminum-alloy sand casings of 195-T4, 195-T6, and 356-T6 to evaluate the bearing strength and tensile properties of the alloys. Comparisons with individually cast bars and specimens machined from slabs indicate that size and form of casing may have a significant effect on mechanical properties. Results of the tensile, compressive, and shear tests are provided in charts and include specified minimum and typical properties for comparison.
Date: August 1948
Creator: Moore, R. L.
Item Type: Refine your search to only Report
open access

Bearing tests of 14S sheet and plate

Description: From Summary: "Tests were made to determine bearing yield and ultimate strengths of bare and Alclad 15S-W(exp 1) and 14S-T(exp 1) sheet and plate in thicknesses of 0.064 inch, 0.250 inch, and 0.750 inch. From the results of these tests it was concluded that the ratios of bearing to tensile properties from the with-grain direction were essentially the same as proposed in NACA TN Nos. 901, 920, 974, and 981 for other high-strength aluminum-alloy sheet and plate."
Date: August 1948
Creator: Moore, R. L.
Item Type: Refine your search to only Report
open access

Calculated Condenser Performance for a Mercury-Turbine Power Plant for Aircraft

Description: "As part of an investigation of the application of nuclear energy to various types of power plants for aircraft, calculations have been made to determine the effect of several operating conditions on the performance of condensers for mercury-turbine power plants. The analysis covered 8 range of turbine-outlet pressures from 1 to 200 pounds per square inch absolute, turbine-inlet pressures from 300 to 700 pounds per square inch absolute,and a range of condenser cooling-air pressure drops, airpla… more
Date: August 27, 1948
Creator: Doyle, Ronald B.
Item Type: Refine your search to only Report
open access

Calibration of Air-Flow Meters for J33 Compressor Investigation

Description: Flow-metering devices used by the NACA and by the manufacturer of the J33 turbojet engine were calibrated together to determine whether an observed discrepancy in weight flow of approximately 4 percent for the two separate investigations might be due to the different devices used to meter air flow. A commercial adjustable orifice and a square-edge flat-plate orifice used by the NACA and a flow nozzle used by the manufacturer were calibrated against surveys across the throat of the nozzle. It wa… more
Date: August 16, 1948
Creator: Kovach, Karl & Withee, Joseph R., Jr.
Item Type: Refine your search to only Report
open access

Characteristics of Low-Aspect Ratio Wings at Supercritical Mach Numbers

Description: Note presenting experiments to study the characteristics of low-aspect-ratio wings at supercritical Mach numbers. The experiments consisted of tests of wings of aspect ratios ranging from infinity to 2. The results indicate that the detrimental effects of compressibility in the supercritical speed range on the stability and performance of aircraft are alleviated to a great degree by the use of low-aspect-ratio lifting surfaces.
Date: August 1948
Creator: Stack, John & Lindsey, W. F.
Item Type: Refine your search to only Report
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