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Effect of Dissolved Oxygen on the Filterability of Jet Fuels for Temperatures Between 300 Degrees and 400 Degrees Fahrenheit

Description: "The effect of dissolved oxygen in the filter-clogging characteristics of three JP-4 and two JP-5 fuels was studied at 300 degrees to 400 degrees F in a bench- scale rig, employing filter paper as the filter medium. The residence time of the fuel at the high temperature was approximately 6 seconds" (p. 1).
Date: December 28, 1955
Creator: McKeown, Anderson B. & Hibbard, Robert R.
Partner: UNT Libraries Government Documents Department
open access

A Bibliography of NACA Reports on Control of Turbojet Engines

Description: Memorandum presenting an annotated bibliography of NACA reports containing information of interest to designers and manufacturers of controls for turbojet engines. The eleven major topics include starting, acceleration, flame-out, temperature control, stability and dynamics of small disturbances, combustion dynamics, engine inlet diffuser control, steady-state engine performance, fuel systems, sensors, and general control system theory.
Date: June 28, 1956
Creator: Sanders, John C.
Partner: UNT Libraries Government Documents Department
open access

Full-Scale Evaluation of Some Flameholder Design Concepts for High-Inlet-Velocity Afterburners

Description: Memorandum presenting an investigation of a full-scale afterburner with high burner-inlet velocity conducted to determine burner performance with several variations in burner design. Variables receiving particular attention were flameholder design and burner length. Results regarding diffuser performance, performance of the reference two-V-gutter flameholder, designs to improve combustion for high-velocity conditions, and operational characteristics are provided.
Date: June 28, 1956
Creator: Prince, William R.; Velie, Wallace W. & Braithwaite, Willis M.
Partner: UNT Libraries Government Documents Department
open access

Full-scale, free-jet investigation of methods of improving outlet flow distribution in a side-inlet supersonic diffuser

Description: Report presenting a full-scale, free-jet investigation to determine the performance of a side-inlet supersonic diffuser designed for a flight Mach number of 2.75. Several internal modifications made to improve diffuser-outlet flow uniformity were also evaluated. Results regarding the general characteristics of the diffuser and effect of diffuser modifications on flow distribution are provided.
Date: March 28, 1955
Creator: Farley, John M. & Seashore, Ferris L.
Partner: UNT Libraries Government Documents Department
open access

Comparison of Various Heat Exchangers for Liquid-Metal Nuclear Turbojet Over Range of Flight and Operating Conditions

Description: Memorandum presenting an analysis of a large number of liquid-metal-to-air heat-exchanger cores for the nuclear-powered liquid-metal turbojet cycle to determine which types yield the best overall net thrust per total engine weight. The performances of all exchangers considered were initially evaluated at a median condition. The performance of the best of each of the four types was compared with that of a shell-and-tube exchanger with the air flowing through the tubes, operating at the same cond… more
Date: April 28, 1958
Creator: Ragsdale, Robert G.
Partner: UNT Libraries Government Documents Department
open access

Performance of a Blunt-lip Side Inlet With Ramp Bleed, Bypass, and a Long Constant-area Duct Ahead of the Engine- Mach Numbers 0.66 and 1.5 to 2.1

Description: Report presenting the performance of a side inlet with a fixed 12 degree two-dimensional compression surface for a range of Mach numbers, angles of attack, and yaw. The effects of several methods of compression-surface boundary-layer removal were investigated as well as a solid ramp.
Date: December 28, 1956
Creator: Allen, John L.
Partner: UNT Libraries Government Documents Department
open access

Attenuation of Tangential-Pressure Oscillations in a Liquid-Oxygen-n-Heptane Rocket Engine With Longitudinal Fins

Description: Attenuation of tangent-pressure oscillation in liquid-oxygen-heptane rocket engine combustion chamber using longitudinal fin. Results regarding the engine performance with injector A, effect of fins with injector A, and destructiveness of screaming are provided.
Date: June 28, 1956
Creator: Priem, Richard J.
Partner: UNT Libraries Government Documents Department
open access

An Investigation of Convergent-Divergent Diffusers at Mach Number 1.85

Description: An investigation has been conducted in the Cleveland 18- by 18-inch supersonic tunnel at a Mach number of 1.85 and angles of attack from 0 deg to 5 deg to determine optimum design configurations for a convergent-divergent type of supersonic diffuser with a subsonic diffuser of 5 deg included divergence angle. Total pressure recoveries in excess of theoretical recovery across a normal shock at a free-stream Mach number of 1.85 wore obtained with several configurations.
Date: April 28, 1947
Creator: Wyatt, DeMarquis D. & Hunczak, Henry R.
Partner: UNT Libraries Government Documents Department
open access

Performance of High-Pressure-Ratio Axial-Flow Compressor Using Highly Cambered Naca 65-Series Blower Blades at High Mach Numbers

Description: "A complete stage of an axial-flow compressor was designed and built to investigate the possibility of obtaining a high pressure ratio with an acceptable efficiency through the use of the optimum combination of high blade loading and high relative inlet Mach number. Over-all stage performance was investigated over a range of flows at equivalent tip speeds of 418 to 836 feet per second. At design speed (836 ft/sec), a peak total-pressure ration of 1.445 was obtained with an adiabatic efficiency … more
Date: March 28, 1950
Creator: Voit, Charles H.; Guentert, Donald C. & Dugan, James F.
Partner: UNT Libraries Government Documents Department
open access

Altitude performance and operational characteristics of 29-inch-diameter tail-pipe burner with several fuel systems and fuel-cooled stage-type flame holders on J35-A-5 turbojet engine

Description: An investigation of tail-pipe burning was conducted in the NACA Lewis altitude wind tunnel with a full-scale turbojet engine and an 29-inch-diameter tail-pipe burner. Effects of fuel distribution and number and arrangement of stages on performance and operational characteristics of several fuel-cooled flame holders are presented and discussed. Operation with a three-stage flame holder having the large stage upstream was the most efficient. Combustion efficiency was slightly increased at high al… more
Date: April 28, 1950
Creator: Golladay, Richard L. & Bloomer, Harry E.
Partner: UNT Libraries Government Documents Department
open access

Investigation of the diborane - hydrogen peroxide propellant combination

Description: Report presenting the results of two runs made with liquid diborane and hydrogen peroxide in a small-scale rocket engine. The first run was very erratic and modifications were made to the testing apparatus and procedures for the second run. In the second run, the combustion started immediately and continued smoothly for 12 seconds of operation.
Date: May 28, 1948
Creator: Rowe, William H.; Ordin, Paul M. & Diehl, John M.
Partner: UNT Libraries Government Documents Department
open access

Fundamental flame velocities of pure hydrocarbons 1: alkanes, alkenes, alkynes benzene, and cyclohexane

Description: The flame velocities of 37 pure hydrocarbons including normal and branched alkanes, alkenes, and alkynes; as well as benzene and cyclohexane, together with the experimental technique employed are presented. The normal alkanes have about the same flame velocity from ethane through heptane with methane being about 16 percent lower. Unsaturation increases the flame velocity in the order of alkanes, alkenes, and alkynes. Branching reduces the flame velocity.
Date: September 28, 1950
Creator: Gerstein, Melvin; Levine, Oscar & Wong, Edgar L.
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine 12: Cooling Effectiveness of a Blade With an Insert and With Fins Made of a Continuous Corrugated Sheet

Description: Memorandum presenting an investigation conducted in a modified turbojet engine to determine the cooling effectiveness of an air-cooled turbine-rotor blade employing a corrugated metal sheet brazed to the inner surface of the blade shell to increase the internal heat-transfer area. The corrugated fin blade had a lower integrated average wall temperature at the section investigated than the more promising shell-supported blade types previously investigated. Results regarding the temperature distr… more
Date: August 28, 1952
Creator: Bartoo, Edward R. & Clure, John L.
Partner: UNT Libraries Government Documents Department
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Effect of Free Methyl Radicals on Slow Oxidation of Propane and Ethane

Description: Memorandum presenting a study of the effect of free methyl radicals on the slow oxidation of both ethane and propane by means of a photochemical decomposition reaction in a static system. The introduction of methyl radicals into a mixture of propane and oxygen or ethane and oxygen substantially lowered the initiation temperature of the combustion of the hydrocarbon.
Date: August 28, 1952
Creator: McDonald, Glen E. & Schalla, Rose L.
Partner: UNT Libraries Government Documents Department
open access

Matched performance characteristics of a 16-stage axial-flow compressor and a 3-stage turbine

Description: Report presenting component performance data for one modification of a 16-stage compressor and a 3-stage turbine to determine the matched performance characteristics of an engine with those components. The compressor surge line and infinite exhaust-nozzle-area equilibrium operating line restricted the region of matched compressor-turbine operation. Results regarding the engine operation with modified compressor and three-stage turbine, effect of leakage on engine operation, component efficienci… more
Date: April 28, 1953
Creator: Rebeske, John J., Jr. & Dugan, James F., Jr.
Partner: UNT Libraries Government Documents Department
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Combustion properties of aluminum as ram-jet fuel

Description: Report presenting an experimental investigation to determine the combustion properties of aluminum as a fuel for use in high-speed aircraft. The aluminum fuel was injected both in powder and wire form into 2-inch-diameter ramjet-type combustors. Results regarding operational problems, thrust, and combustion efficiency are provided.
Date: March 28, 1951
Creator: Branstetter, J. Robert; Lord, Albert M. & Gerstein, Melvin
Partner: UNT Libraries Government Documents Department
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Force and Pressure Characteristics for a Series of Nose Inlets at Mach Numbers From 1.59 to 1.99 4: Conical-Spike External-Internal Compression Inlet Utilizing Perforated Cowl

Description: Report presenting testing conducted to determine the force and pressure-recovery characteristics of a model utilizing a single-shock spike-type inlet with a perforated cowl. The use of the cowl resulted in the attainment of a high pressure recovery at zero angle of attack, but it was accompanied by a relatively large increase in external drag as compared with nonperforated inlets of the same proportions. Results regarding the characteristics at zero angle of attack, effects of changes in angle … more
Date: March 28, 1951
Creator: Madden, Robert T. & Kremzier, Emil J.
Partner: UNT Libraries Government Documents Department
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Evaluation of operating characteristics of a supersonic free-jet facility for full-scale ram-jet investigations

Description: From Summary: "A supersonic free-jet facility (Mach number 3) capable of accommodating full-scale ram-jet engines has been constructed and evaluated. A 24-inch circular nozzle produces a jet of sufficiently uniform velocity that a good simulation of the engine internal flow is obtained. An annular diffuser placed around the engine recovers part of the total pressure of the jet flow passing outside the engine so that the pressure ratios which must be imposed across the facility to start and main… more
Date: October 28, 1952
Creator: Wentworth, Carl B.; Hurrell, Herbert G. & Nakanishi, Shigeo
Partner: UNT Libraries Government Documents Department
open access

Starting characteristics and combustion performance of magnesium slurry in 6.5-inch-diameter ram-jet engine mounted in connected-pipe facility

Description: The starting characteristics and combustion performance of slurry type fuels, consisting of 50 percent magnesium powder in a hydrocarbon carrier, have been investigated in a flight-type, 6.5-inch-diameter ram-jet engine in a connected-pipe facility. Quick, dependable starting of the engine was obtained by the use of a disk which blocked part of the combustor area downstream of the flame holder. Acceptable performance was achieved with a short fuel-air mixing length by the development of a fuel-… more
Date: January 28, 1954
Creator: Gibbs, James B.
Partner: UNT Libraries Government Documents Department
open access

Performance characteristics at Mach numbers to 2.0 of various types of side inlets mounted on fuselage of proposed supersonic airplane 4: rectangular cowl inlets with two-dimensional compression ramps

Description: Report presenting an experimental investigation to determine the performance of side inlets with external compression ramps and rectangular cowls mounted on the fuselage forebody of a proposed supersonic airplane. Results regarding supersonic Mach number range, subsonic Mach number of 0.63, and static or take-off conditions are provided.
Date: October 28, 1952
Creator: Simon, Paul C.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Blade-Row Flow Distributions in Axial-Flow-Compressor Stage Consisting of Guide Vanes and Rotor-Blade Row

Description: "A 30-inch tip-diameter axial-flow compressor stage was investigated with and without rotor to determine individual blade-row performance, interblade-row effects, and outer-wall boundary-layer conditions. Velocity gradients at guide-vane outlet without rotor approximated design assumptions, when the measured variation of leaving angle was considered. With rotor in operation, Mach number and rotor-blade effects changed flow distribution leaving guide vanes and invalidated design assumption of ra… more
Date: November 28, 1950
Creator: Mahoney, John J.; Dugan, Paul D.; Budinger, Raymond E. & Goelzer, H. Fred
Partner: UNT Libraries Government Documents Department
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Free-Flight Performance of 16-Inch-Diameter Supersonic Ram-Jet Units 3: Four Units Designed for Combustion-Chamber-Inlet Mach Number of 0.245 at Free-Stream Mach Number of 1.8 (Units D-1, D-2, D-3, and D-4)

Description: Performance of four 16-inch-diameter ram-jet units was determined at free-stream Mach numbers of 0.49 to 1.78 over range of gas total-temperature ratios of 1.0 to 6.1. Time histories of each flight and data on thrust, drag, diffuser efficiency, and combustion are presented. A maximum thrust coefficient of 0.88 and a maximum net acceleration of 5.13 g's were observed for the four units.
Date: June 28, 1950
Creator: Disher, John H. & Rabinowitz, Leonard
Partner: UNT Libraries Government Documents Department
open access

Performance of an impulse-type supersonic compressor with stators

Description: Report presenting testing of an impulse-type supersonic compressor rotor with stators tested in Freon-12 over a range of equivalent tip speeds and weight flows. A static pressure ratio of 1.83 and an efficiency of 84.7 percent were obtained at 69.1 percent of the design speed of 1604 feet per second in air.
Date: April 28, 1952
Creator: Klapproth, John F.; Ullman, Guy N. & Tysl, Edward R.
Partner: UNT Libraries Government Documents Department
open access

Comparison of High-Speed Operating Characteristics of Size 215 Cylindrical-Roller Bearings as Determined in Turbojet Engine and in Laboratory Test Rig

Description: "A comparison of the operating characteristics of 75-millimeter-bore (size 215) cylindrical-roller one-piece inner-race-riding cage-type bearings was made using a laboratory test rig and a turbojet engine. Cooling correlation parameters were determined by means of dimensional analysis, and the generalized results for both the inner- and outer-race bearing operating temperatures are compared for the laboratory test rig and the turbojet engine. Inner- and outer-race cooling-correlation curves wer… more
Date: November 28, 1951
Creator: Macks, E. Fred & Nemeth, Zolton N.
Partner: UNT Libraries Government Documents Department
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