Technical Report Archive & Image Library (TRAIL) - 330 Matching Results

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Effect of chord size on weight and cooling characteristics of air-cooled turbine blades

Description: An analysis has been made to determine the effect of chord size on the weight and cooling characteristics of shell-supported, air-cooled gas-turbine blades. In uncooled turbines with solid blades, the general practice has been to design turbines with high aspect ratio (small blade chord) to achieve substantial turbine weight reduction. With air-cooled blades, this study shows that turbine blade weight is affected to a much smaller degree by the size of the blade chord.
Date: November 13, 1956
Creator: Esgar, Jack B.; Schum, Eugene F. & Curren, Arthur N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of design changes and operating conditions on combustion and operational performance of a 28-inch diameter ram-jet engine

Description: The results of an altitude test-chamber investigation of the effects of a number of design changes and operating conditions on altitude peformance of a 28-inch diameter ram jet engine are presented. Most of the investigation was for a simulated flight Mach number of 2.0 above the tropopause. Fuel-air distribution, gutter width, the presence of a pilot flame, cimbustion-chamber-inlet temperature, and exhaust-nozzle throat area were found to have significant effects on limits of combustion. Combu… more
Date: February 13, 1952
Creator: Shillito, T. B. & Nakanishi, Shigeo
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Design Changes of Operating Conditions on Combustion and Operational Performance of a 28-Inch Diameter Ram-Jet Engine

Description: Report presenting an investigation of the altitude performance of a 28-inch diameter ram-jet engine using a direct-connect system in an altitude test chamber. The majority of the investigation occurred at Mach number 2 at altitudes above the tropopause (250 degrees Fahrenheit inlet temperature). Various design configurations were explored and runs were made with different types of fuel.
Date: February 13, 1952
Creator: Shillito, T. B. & Nakanishi, Shigeo
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Fuel-Air Ratio Concentration in Combustion Zone on Combustion Performance of a 16-Inch Ram-Jet Engine

Description: The results of fuel-air ratio and temperature surveys made in the flame stabilizing zone of a 16-inch ram-jet combustor indicated that the distribution of combustible mixture immediately downstream of a flame holder should be mechanically controlled if a preferred mixture composition is to be maintained in that zone. A sloping-baffle combustor configuration gave combustion efficiencies of 90 percent or greater over a range of fuel-air ratios from 0.010 to 0.045.
Date: April 13, 1953
Creator: Cervenka, A. J.; Bahr, D. W. & Dangle, E. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of fuel volatility characteristics on ignition-energy requirements in a turbojet combustor

Description: Report presenting an investigation to determine the effect of fuel volatility characteristics on the minimum spark energy required to ignite a single tubular turbojet-engine combustor. Results regarding the ignition at sea-level conditions, ignition at altitude conditions, relation between distillation data and minimum ignition-energy requirements, and application of relation to data from a previous investigation are provided.
Date: January 13, 1953
Creator: Foster, Hampton H. & Straight, David M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of inlet aspect ratio on the starting and pressure recovery characteristics of a rectangular swept scoop inlet tested at a Mach number of 3.1

Description: Report presenting an experimental investigation of a rectangular swept scoop inlet designed for and tested at a free-stream Mach number of 3.1 to determine the effect of inlet aspect ratio on the minimum inlet starting concentration ratio and the resulting inlet total-pressure recovery. Results regarding the determination of the starting contraction ratio, effect of inlet aspect ratio on the inlet starting characteristics, total-pressure recovery and mass-flow variations, and effects of inlet a… more
Date: January 13, 1958
Creator: Mackley, Ernest A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of liner air-entry holes, fuel state, and combustor size on performance of an annular turbojet combustor at low pressures and high air-flow rates

Description: Report presenting the development of an annular combustor by utilizing the design principles evolved in previous investigations and by making 12 design changes to optimize the altitude performance of the combustor. Three types of fuels were used and the combustion efficiency, pressure losses, and outlet temperature profiles were evaluated.
Date: January 13, 1953
Creator: Norgren, Carl T. & Childs, J. Howard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Magnitude of Vibratory Load Superimposed on Mean Tensile Load on Mechanism of and Time to Fracture of Specimens and Correlation to Engine Blade

Description: Memorandum presenting tensile fatigue tests run on seven turbine-blade alloys at a temperature of 1500 degrees Fahrenheit and a mean stress of 22,000 pounds per square inch with superimposed alternating stresses of 0, 5000, 10,000, and 15,000 pounds per square inch. The same three types of fracture occurring in turbine blades - stress-rupture, stress-rupture followed by fatigue, and fatigue - were obtained in the specimens. Results regarding the effect of alternating stress on mechanism of fail… more
Date: November 13, 1952
Creator: Ferguson, Robert R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of NACA Injection Impeller and Ducted Head Baffles on Flight Cooling Performance of Double-Row Radial Engine in Four-Engine Heavy Bomber

Description: "The NACA has conducted a flight investigation to improve the cooling characteristics of the installation of a double-row radial engine. The tests reported herein concern the use of the NACA injection impeller and ducted head baffles in various combinations on both the port inboard and the port outboard engines. The performance of the modified installation was evaluated by comparing it with that of the standard engines" (p. 1).
Date: April 13, 1945
Creator: Marble, Frank E.; Miller, Mahlon A. & Vensel, Joseph R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of oxygen concentration of the inlet oxygen-nitrogen mixture on the combustion efficiency of a single J33 turbojet combustor

Description: Report presenting an investigation to determine the importance of molecular-scale processes in the overall turbojet combustion process. The effect of oxygen concentration on the inlet oxygen-nitrogen mixture on the combustion efficiency of a single J33 combustor was determined for a range of combustor-inlet pressures and a range of fuel-flow rates. At a given fuel-flow rate, combustion efficiency decreased at an increasing rate with reduction in oxygen concentration.
Date: August 13, 1952
Creator: Graves, Charles C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of radiant energy on vaporization and combustion of liquid fuels

Description: Report presenting an investigation of the radiative processes involved in combustion to determine the present role of radiant energy transfer in combustors. The equivalent gray-body emissivity of a hydrocarbon fuel may be increased by use of liquid or solid, soluble or nonsoluble, additives. Results regarding the experimental apparatus and methods, emission characteristics of luminous and nonluminous flames, absorptivity of fuels and of solutions of possible additives, and absorption by slurrie… more
Date: November 13, 1952
Creator: Berlad, A. L. & Hibbard, R. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Section Thickness and Trailing-Edge Radius on the Performance of NACA 65-Series Compressor Blades in Cascade at Low Speeds

Description: Report presenting tests of NACA 65-series compressor blades cambered to an isolated airfoil lift coefficient of 1.2 at several maximum section thicknesses to obtain the effect of maximum section thickness on section operating characteristics. Information about surface pressure trends, design angle-of-attack selection, drag, operating range, and critical Mach number is also provided. Changing the section thickness was not found to significantly affect the design angle of attack selected.
Date: December 13, 1951
Creator: Herrig, L. Joseph; Emery, James C. & Erwin, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Supercharger Capacity on Engine and Airplane Performance

Description: This report presents the results of an investigation to determine the effect of different supercharger capacities on the performance of an airplane and its engine . The tests were conducted on a DH4-M2 airplane powered with a Liberty 12 engine. In this investigation four supercharger capacities, obtained by driving a roots type supercharger at 1.615, 1.957, 2.4, and 3 time engine speed, were used to maintain sea-level pressure at the carburetor to altitudes of 7,000, 11,500, 17,000, and 22,000 … more
Date: March 13, 1929
Creator: Schey, O. W. & Gove, W. D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Target-Type Thrust Reverser on Transonic Aerodynamic Characteristics of a Single-Engine Fighter Model

Description: A brief investigation of a target-type thrust reverser on a single-engine fighter model has been conducted in the Langley 16-foot transonic tunnel at Mach numbers from 0.20 to 1.05. At Mach numbers of 0.80, 0.92, and 1.05, a hydrogen peroxide turbojet-engine simulator was operated with the thrust reverser extended. The angle of attack was varied from 0 degrees to 5 degrees at these Mach numbers.
Date: January 13, 1958
Creator: Swihart, John M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of temperature on performance of several ejector configurations

Description: Report presenting an investigation to determine the effect of the primary-jet temperature on the performance of several ejector configurations. The performance of ejectors expressed in terms of the ratio of weight of secondary air flow to primary air flow was found to be affected by temperature in two ways.
Date: June 13, 1949
Creator: Wilsted, H. D.; Huddleston, S. C. & Ellis, C. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Viscosity on Fuel Leakage Between Lapped Plungers and Sleeves and on the Discharge From a Pump-Injection System

Description: "Test data and analysis show that the rate of fuel leakage between a lapped plunger and sleeve varies directly with the density of the fuel, the diameter of the plunger, the pressure producing the leakage, and the cube of the mean clearance between the plunger and sleeve. The rate varies inversely as the length of the lapped fit and the viscosity of the fuel. With a mean clearance between the plunger and sleeve of 0.0001 inch the leakage amounts to approximately 0.2 percent of the fuel injected… more
Date: December 13, 1933
Creator: Rothrock, A. M. & Marsh, E. T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effectiveness of Thermal-Pneumatic Airfoil-Ice-Protection System

Description: From Summary: "Icing and drag investigations were conducted in the NACA Lewis icing research tunnel employing a combination thermal-pneumatic de-icer mounted on a 42-inch-chord NACA 0018 airfoil. The de-icer consisted of a 3-inch-wide electrically heated strip symmetrically located about the leading edge with inflatable tubes on the upper and lower airfoil surfaces aft of the heated area. The entire de-icer extended to approximately 25 percent of chord. A maximum power density of 9.25 watts per… more
Date: April 13, 1951
Creator: Gowan, William H., Jr. & Mulholland, Donald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of External Store-Pylon Configuration and Position on the Aerodynamic Characteristics of a 45 Degree Swept Wing-Fuselage Combination at a Mach Number of 1.61

Description: Report presenting an investigation of a pylon-mounted-store airplane configuration in the supersonic pressure tunnel at a Mach number of 1.61. Forces and moments of a complete wing-fuselage-store-pylon combination was measured for a variety of pylon-mounted store locations below the wing. Results regarding the effect of store position on the aerodynamic characteristics in pitch, effect of store position on the aerodynamic characteristics in sideslip, store fins and store tail cone, double-store… more
Date: May 13, 1958
Creator: Morris, Odell A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of Free-Stream Reynolds Number, Engine Installation, and Model Scale on Stability Characteristics of a Translating-Spike Inlet at Mach 2.0

Description: Memorandum presenting the effect of free-stream Reynolds number, engine installation, and model scale on inlet stability limits and on the amplitude and frequency of buzz. The data were taken at a free-stream Mach number of 2.0 and angles of attack from 0 to 6 degrees. Results regarding free-stream Reynolds number effect, model scale, and effect of engine on stability are provided.
Date: November 13, 1957
Creator: Musial, Norman T. & Bowditch, David
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of free-stream Reynolds number, engine installation, and model scale on stability characteristics of a translating-spike inlet at Mach 2.0

Description: Report presenting the effect of free-stream Reynolds number, engine installation, and model scale on inlet stability limits and on the amplitude and frequency of buzz. The data was obtained at mach number 2.0 and a range of angles of attack. Results regarding the free-stream Reynolds number effect, model scale, and effect of engine on stability are provided.
Date: November 13, 1957
Creator: Musial, Norman T. & Bowditch, David
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of Obstructions in Compressor Inlet on Blade Vibration in 10-Stage Axial-Flow Compressor

Description: Report presenting a blade-vibration survey that was conducted during normal operation of a 10-stage axial-flow compressor powered by part of a complete jet engine. Strain-gage records were obtained from all stages during acceleration, deceleration, and constant-speed runs. Results regarding the inlet disturbances and damping characteristics are provided.
Date: February 13, 1950
Creator: Meyer, André J., Jr.; Calvert, Howard F. & Morse, C. Robert
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Elimination of Fire Hazard Due to Back Fires

Description: "A critical study was made of the operation of a type of back-fire arrester used to reduce the fire hazard of aircraft engines. A flame arrester consisting of a pack or plug of alternate flat and corrugated plates of thin metal was installed in the intake pipe of a gasoline engines; an auxiliary spark plug inserted in the intake manifold permitted the production of artificial back fires at will. It was found possible to design a plug which prevented all back fires from reaching the carburetor" … more
Date: October 13, 1931
Creator: Theodorsen, Theodore & Freeman, Ira M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Energy Response And Physical Properties Of NTA* Personnel Neutron Dosimeter Nuclear Track Film

Description: This paper reports the chemical and physical properties of the NTA film packet. It correlates with these properties the response of this packet to neutrons of various energies. In this correlation the concept of the track unit is introduced as a basic unit for reporting film-packet response.
Date: January 13, 1961
Creator: Lehman, Richard L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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