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Flight and preflight evaluation of an automatic thrust-coefficient control system in a twin-engine ram-jet missile

Description: Report presenting a flight and preflight evaluation of an automatic thrust-coefficient control system in a twin-engine ram-jet missile. A flicker-type single-loop servocontrol system is shown to be a usable way of controlling ram-jet thrust coefficients.
Date: January 22, 1954
Creator: Dettwyler, H. Rudolph & Trout, Otto F., Jr.
Partner: UNT Libraries Government Documents Department

Flight test of a solid-fuel ramjet with the internal surface of the combustor air cooled

Description: Report presenting a flight investigation of a rocket-launched solid-fuel ram-jet engine designed to bypass cooling air around the fuel charge. The internally cooled combustor averted combustor burn-out during the flight test. Results regarding the net thrust coefficient, gross thrust coefficient, time history of the air specific impulse, and total fuel load are provided.
Date: July 3, 1956
Creator: Bartlett, Walter A., Jr.
Partner: UNT Libraries Government Documents Department

Initial flight investigation of a twin engine supersonic ram jet

Description: From Summary: "A flight investigation was made of a supersonic twin-ram-jet test vehicle using short-flame-length burners. The test demonstrated a maximum acceleration of 3.6g and a maximum flight Mach number of 3.02. Data were obtained over a Mach number range from about 1.9 to 3.0, an altitude range from 1,800 to 40,900 feet, and a fuel-air-ratio range from 0.012 to 0.065."
Date: September 15, 1950
Creator: Faget, Maxime A. & Dettwyler, H. Rudolph
Partner: UNT Libraries Government Documents Department

Experimental study of shock-positioning method of ram-jet-engine control

Description: Report presenting an investigation of ram-jet-engine control by shock positioning on a 16-inch fixed-geometry ram jet at a range of free-stream Mach numbers. The control method appears to offer adequate control of ram-jet-engine operation. Results regarding the steady-state performance, effect of control settings on response and stability, effect of disturbance size and Mach number on response to fuel-flow disturbances, Mach number disturbances, angle-of-attack disturbances, exhaust-area disturbances, and recovery from subcritical engine operation are provided.
Date: August 29, 1955
Creator: Hurrell, Herbert G.; Vasu, George & Dunbar, William R.
Partner: UNT Libraries Government Documents Department

Preliminary survey of propulsion using chemical energy stored in the upper atmosphere

Description: Ram-jet cycles that use the chemical energy of dissociated oxygen for propulsion in the ionosphere are presented. After a review of the properties and compositions of the upper atmosphere, the external drag, recombination kinetics, and aerodynamic-heating problems of an orbiting ram jet are analyzed. The study indicates that the recombination ram jet might be useful for sustaining a satellite at an altitude of about 60 miles. Atmospheric composition and recombination-rate coefficients were too uncertain for more definite conclusions. The ram jet is a marginal device even in the optimistic view.
Date: May 1958
Creator: Baldwin, Lionel V. & Blackshear, Perry L.
Partner: UNT Libraries Government Documents Department

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

Analysis of rocket, ramjet, and turbojet engines for supersonic propulsion of long-range missiles. 3: Ramjet engine performance

Description: Report presenting ramjet engine performance data over a range of engine design variables to permit selection and evaluation of a ramjet engine configuration for a long-range supersonic missile. Results include engine thrust, drag, fuel consumption, area ratios, and weight, and are suitable for use in design studies of missiles incorporating either internally or externally mounted ramjet engines.
Date: August 5, 1954
Creator: Weber, Richard J. & Luidens, Roger W.
Partner: UNT Libraries Government Documents Department

Experimental investigation of pressure fluctuations in 3.6 inch ram jet at Mach number 1.92

Description: Report presenting an experimental study of the pressure fluctuations at the combustion-chamber inlets of a ramjet operating a Mach number of 1.92 in the supersonic tunnel. Results are presented for two burner configurations of different operating characteristics to indicate trends in pressure magnitude, frequency, and wave form. Results regarding the perforated conical flame holder, regenerative-type burner, and diffuser total-pressure recovery are provided.
Date: October 13, 1949
Creator: Connors, James F. & Schroeder, Albert H.
Partner: UNT Libraries Government Documents Department

Starting and performance characteristics of a large asymmetric supersonic free-jet facility

Description: Report presenting the characteristics of an asymmetric free-jet facility constructed to investigate a 48-inch-diameter ramjet engine and the associated asymmetric supersonic inlet and inlet diffuser. The design flow Mach number of 2.755 could not be established in the free-jet facility with dry inlet air at a temperature of 528 degrees Fahrenheit and overall pressure ratios up to 11.
Date: April 1, 1954
Creator: Seashore, Ferris L. & Hurrell, Herbert G.
Partner: UNT Libraries Government Documents Department

Performance of a 28-inch ramjet utilizing gaseous hydrogen at a Mach number of 3.6, angles of attack up to 12 degree, and pressure altitudes up to 110,000 feet

Description: Report presenting an investigation in the 10- by 10-foot supersonic wind tunnel to evaluate the performance of a shrouded injector burner with perforated domes employed in a 28-inch ramjet using gaseous hydrogen as fuel. Steady-state data were obtained at a pressure altitude of 77,000 feet and zero angle of attack. Results indicated that burning could be initiated under severe distortion conditions and that satisfactory combustor operation was accomplished up to a pressure altitude of 110,000 feet with no adverse effect on combustion efficiency.
Date: May 19, 1958
Creator: Musial, Norman T.; Ward, James J. & Wasserbauer, Joseph F.
Partner: UNT Libraries Government Documents Department

Preflight and flight-test investigation of a 50-percent-magnesium 50-percent JP-4 slurry fuel in a twin engine ram-jet vehicle

Description: Report presenting an investigation conducted by means of preflight and flight tests to determine the performance of a 50-percent-magnesium 50-percent JP-4 slurry fuel in a twin-engine ramjet test vehicle. Data were obtained over a range of Mach numbers. Although a successful flight test was carried out, the performance obtained from preflight testing was below theoretical values.
Date: May 31, 1956
Creator: Trout, Otto F., Jr. & Kennedy, Thomas L.
Partner: UNT Libraries Government Documents Department

Effect of immersed surfaces in combustion zone on efficiency and stability of 5-inch diameter ram-jet combustor

Description: Report presenting an extension of previous work on immersed surfaces in the combustion zone of a ramjet engine. The primary focus was to determine the effect of combustion efficiency and stability of blades located within the immediate wake of a V-gutter flame holder and to find some location and orientation of blades for optimum combustion efficiency and improved stability limits with a minimum of pressure loss.
Date: June 21, 1954
Creator: Reynolds, Thaine W. & Male, Donald W.
Partner: UNT Libraries Government Documents Department

Free-jet performance of 16-inch ram-jet engine with several fuels

Description: Report presenting an investigation of several fuels in a 16-inch ramjet engine during a free-jet investigation of ramjet performance in a wind tunnel. The fuels used were gasoline, kerosene, blend of 50-percent gasoline and 50-percent propylene oxide, blend of 75-percent kerosene and 25-percent propylene oxide, and isopentane. Results regarding ranges of operation, combustion efficiencies, and weight and volume specific fuel consumptions obtained with various fuels.
Date: October 31, 1950
Creator: Wilcox, Fred A.
Partner: UNT Libraries Government Documents Department

Free-flight performance of a rocket-boosted, air-launched 16-inch-diameter ram-jet engine at Mach numbers up to 2.20

Description: From Summary: "The investigation of air-launched ram-jet engines has been extended to include a study of models with a nominal design free-stream Mach number of 2.40. These models require auxiliary thrust in order to attain a flight speed at which the ram jet becomes self-accelerating. A rocket-boosting technique for providing this auxiliary thrust is described and time histories of two rocket-boosted ram-jet flights are presented. In one flight, the model attained a maximum Mach number of 2.20 before a fuel system failure resulted in the destruction of the engine. Performance data for this model are presented in terms of thrust and drag coefficients, diffuser pressure recovery, mass-flow ratio, combustion efficiency, specific fuel consumption, and over-all engine efficiency."
Date: February 3, 1953
Creator: Disher, John H.; Kohl, Robert C. & Jones, Merle L.
Partner: UNT Libraries Government Documents Department

Free-flight performance of 16-inch diameter supersonic ram-jet units 4: 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

Description: Report presenting an investigation of 16-inch-diameter ram-jet units under free-flight conditions to determine performance at high subsonic, transonic, and supersonic velocities. Full-scale units were released from the airplane at high altitudes and accelerated by the engine thrust and force of gravity. Results regarding the diffuser total-pressure recovery, drag, thrust coefficient, and combustion are provided.
Date: February 26, 1951
Creator: Rabb, Leonard & North, Warren J.
Partner: UNT Libraries Government Documents Department

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 maintain the jet are kept to reasonable values."
Date: October 28, 1952
Creator: Wentworth, Carl B.; Hurrell, Herbert G. & Nakanishi, Shigeo
Partner: UNT Libraries Government Documents Department

Performance of a 16-inch ram-jet engine with a can-type combustor at Mach numbers of 1.50 to 2.16

Description: Report presenting an investigation in the supersonic wind tunnel to evaluate the performance of a 16-inch ramjet engine using a can-type-combustor configuration. Data were obtained over a range of fuel-air ratios, free-stream Mach numbers, and angles of attack. Combustion efficiencies were generally unaffected by free-stream Mach number and varied between 60 and 90 percent with JP-4 fuel.
Date: August 27, 1954
Creator: Hearth, Donald P. & Perchonok, Eugene
Partner: UNT Libraries Government Documents Department

Investigation of an on-off inlet shock-position control on a 16-inch ram-jet engine

Description: Report presenting an investigation of a shock-positioning control on a 16-inch ramjet engine at a range of Mach numbers and angles of attack in the supersonic wind tunnel. The control operated at all conditions under which the engine could be manually operated. Prediction of the control-system dynamic behavior can be applied by treating the system as having pure dead time.
Date: November 29, 1954
Creator: Wilcox, Fred A.; Perchonok, Eugene & Hearth, Donald P.
Partner: UNT Libraries Government Documents Department

Summary of free-flight performance of a series of ram-jet engines at Mach numbers from 0.80 to 2.20

Description: From Summary: "Data obtained from the NACA air-launched ram-jet program are summarized with emphasis placed upon the transonic propulsive thrust potential of the engines. Data are presented for boosted and non-boosted engine configurations which incorporate a single-oblique-shock or double-oblique-shock diffuser designed for critical inlet operation at flight Mach numbers of 1.8 and 2.4, respectively. The engines are evaluated in terms of flight Mach number, mass-flow ratio, diffuser pressure recovery, combustion-chamber heat release, propulsive thrust, external drag, and specific impulse. From specific impulse considerations, it appears that for some air-launched missile applications the self-accelerating supersonic ram jet may have a lower gross weight than a rocket-boosted ram jet."
Date: February 11, 1954
Creator: North, Warren J.
Partner: UNT Libraries Government Documents Department

Investigation at zero angle of attack of a 16-inch ram jet engine in 8- by 6-foot supersonic wind tunnel

Description: Report presenting a study in the 8- by 6-foot supersonic wind tunnel of the performance of a 16-inch ramjet engine at zero angle of attack and over a range of free-stream Mach numbers between 1.5 and 2.0. Results regarding diffuser performance, drag evaluation, engine evaluation, and burner performance are provided.
Date: March 2, 1951
Creator: Nussdorfer, T.; Wilcox, F. & Perchonok, E.
Partner: UNT Libraries Government Documents Department

Altitude-test-chamber investigation of performance of a 28-inch ram-jet engine I: combustion and operational performance of four combustion-chamber configurations

Description: 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.
Date: August 23, 1950
Creator: Jones, W. L.; Shillito, T. B. & Henzel, J. G., Jr.
Partner: UNT Libraries Government Documents Department

Preflight tests and flight performance of a 6.5-inch diameter ram-jet engine

Description: Report presenting testing of a 20 degree semiangle conical-inlet ramjet engine with a design Mach number of 2.13 in free supersonic jets to determine the inlet and combustion performance over a fuel-air ratio and Mach number range. Results regarding preflight and flight testing are provided.
Date: November 2, 1953
Creator: Hinners, Arthur H., Jr. & Foland, Douglas H.
Partner: UNT Libraries Government Documents Department

Pentaborane combustion performance in 9.75-inch-diameter ram-jet engine in connected-pipe altitude facility

Description: Report presenting an investigation of the performance of pentaborane fuel in a flight-type, 9.75-inch-diameter ramjet engine mounted in a connected-pipe altitude facility. Combustor efficiency was above 85 percent throughout the range of test conditions. Results regarding the connected-pipe performance and estimated flight performance are provided.
Date: March 13, 1957
Creator: Fivel, Herschel J.; Tower, Leonard K. & Gibbs, James B.
Partner: UNT Libraries Government Documents Department