Technical Report Archive & Image Library (TRAIL) - 269 Matching Results

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Altitude Performance of AN-F-58 Fuels in British Rolls-Royce Nene Single Combustor

Description: "An investigation was conducted with a single combustor from a British Rolls-Royce Nene turbojet engine to determine the altitude performance characteristics of AN-F-58 fuels. Three fuel blends conforming to AN-F-58 specifications were prepared in order to determine the influence of fuel boiling temperatures and aromatic content on combustion efficiencies and altitude operational limits. The performance of the three AN-F-58 fuels was compared in the range of altitudes from sea level to 65,000 f… more
Date: July 8, 1949
Creator: Cook, William P. & Koch, Richard G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude performance of AN-F-58 fuels in J33-A-21 single combustor

Description: Report discussing three fuels conforming to AN-F-58 specification were investigated in order to determine the influence of boiling temperatures and aromatic content on altitude performance in single combustor of a 4600-pound-thrust turbojet engine.
Date: April 8, 1949
Creator: Dittrich, Ralph T. & Jackson, Joseph L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude-Test-Chamber Investigation of McDonnell Afterburner on J34 Engine

Description: "An altitude-test-chamber investigation was conducted to determine the operational and performance characteristics of a McDonnell afterburner with a fixed-area exhaust nozzle on a J34 engine. At rated engine speed, the altitude limit, as determined by combustion blow-out, occurred as a band of unstable operation of about 6000-foot altitude in width with minimum altitude limits from 31,000 feet at a simulated flight Mach number of 0.40 to about 45,500 feet at a simulated flight Mach number of 1.… more
Date: June 2, 1949
Creator: Reller, John O. & Dowman, Harry W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude-wind-tunnel investigation of AN-F-58 fuel in experimental version of J47 turbojet engine

Description: An altitude-wind-tunnel investigation of the performance of AN-F-58 and AN-F-32 fuels in an experimental turbojet engine was conducted over a range of simulated altitudes and flight Mach numbers. Combustion efficiencies obtained with AN-F-58 and AN-F-32 fuels were approximately equal. The minimum-speed altitude operational limit was essentially the same with either AN-F-58 or AN-F-32 fuel. Starting characteristics of the two fuels were approximately the same at low wind milling speeds. Visual o… more
Date: May 2, 1949
Creator: Meyer, Carl L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude-wind-tunnel investigation of compressor performance on J47 turbojet engine

Description: From Introduction: "The effects of variations in altitude, flight Mach number, and exhaust-nozzle-outlet area on the compressor performance characteristics are graphically presented. A complete tabulation of the compressor performance data is also presented."
Date: November 22, 1949
Creator: Prince, William R. & Jansen, Emmert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude-wind-tunnel investigation of J47 turbojet-engine performance

Description: From Introduction: "Data are presented in graphical form to show the engine performance over a range of altitudes from 5000 to 50,000 feet and flight Mach numbers from 0.21 to 0.97. Curves are presented to show the windmilling characteristics of the engine. All engine performance data obtained in the investigation are also presented in tabular form."
Date: November 15, 1949
Creator: Conrad, E. William & Sobolewski, Adam E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude-wind-tunnel investigation of various can-type burners in Bumblebee 18-inch ram jet

Description: An investigation on various can-type burners in a Bumblebee 18-inch ram jet under controlled conditions of pressure altitude and ram pressure ratio was conducted in the NACA Lewis altitude wind tunnel with kerosene as fuel. The performance of the following can-type burner configurations was better than that of the other burner configurations investigated: (1) a flame holder having a two-pitch alinement of perforations, 0.07-inch-wide cooling slots, and an arrangement of fuel nozzles located wit… more
Date: March 16, 1949
Creator: Dupree, D. T.; Nussdorfer, T. J. & Sterbentz, W. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis and Experimental Observation of Pressure Losses in Ram-Jet Combustion Chambers

Description: From Introduction: "Some experimental data on flame-holder pressure losses have been presented (reference 1 to 4). A theoretical analysis that assume a sudden enlargement of flow area was made at the NACA Lewis laboratory to determine the effect of flame-holder open area and combustion-chamber-inlet Mach number on the pressure losses across flame holders. The results of this analysis were then compared with experimental data obtained with several different flame-holder designs."
Date: November 4, 1949
Creator: Sterbentz, William H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An analysis of a highly compounded two-stroke-cycle compression-ignition engine

Description: This report presents an analysis of a compound engine operating with manifold pressures ranging from 60 to 110 lb/sq in. absolute and discusses the effects of engine limits (peak cylinder pressure and turbine-inlet temperature) and component efficiency.
Date: April 4, 1949
Creator: Tauschek, Max J.; Sather, Bernard I. & Biermann, Arnold E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Analysis of Airspeeds Attained by a Douglas DC-4 Airplane in Commercial Operations During the Early Months of 1947

Description: Report presenting airspeed and altitude data for nonscheduled cargo operations of a Douglas DC-4 airplane between Seattle, Washington and Alaska during February and March of 1947 to determine the probability of reaching or exceeding given values of airspeed and Mach number. The total probability of exceeding a placard never-exceed speed of 266 mph depends primarily on exceeding the speed in descent. The probability was found to be about once in 100 hours of descent or once in 1000 hours of gene… more
Date: October 6, 1949
Creator: Steiner, Roy
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An analysis of available data on effects of wing-fuselage-tail and wing-nacelle interference on the distribution of the air load among components of airplanes

Description: From Introduction: "The purpose of the present paper is to summarize the available data on the effects of wing-fuselage-tail and wing-nacelle interference on the distribution of the air load among aircraft components. Some discussion is also given of the effects of center-of-gravity position."
Date: April 11, 1949
Creator: Wollner, Bertram C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of measured pressures on airfoils at Mach numbers near 1

Description: Report presenting measured pressure over airfoils at Mach number 1, with subsonic velocities at the nose and supersonic velocities throughout the rear portion, are analyzed by comparison with calculations for similar cases. Results regarding the theoretical basis of approximation, comparison of Prandtl-Meyer flow with measurements, comparison of linear-velocity extrapolation with measurements, and effect of boundary layer upon airfoil pressures are provided.
Date: September 19, 1949
Creator: Habel, Louis W. & Miller, Mason F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of the dynamic lateral stability characteristics of the Bell X-2 airplane as affected by variations in mass, aerodynamic, and dimensional parameters

Description: Report presenting an analysis of the dynamic-lateral-stability characteristics of the Bell X-2 airplane as affected by variations in mass, aerodynamic, and dimensional parameters by means of calculations of the period and rate of damping of the lateral oscillation. Results regarding the airplane with flaps and gear retracted, airplane with flaps and gear lowered, and effects of assumed modifications to the airplane are provided.
Date: August 10, 1949
Creator: Michael, W. H., Jr. & Queijo, M. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of the Effects of Various Mass, Aerodynamic, and Dimensional Parameters on the Dynamic Lateral Stability of the Douglas D-558-2 Airplane

Description: Report presenting an investigation of the effects of various mass, aerodynamic, and dimensional parameters on the dynamic lateral stability of the Douglas D-558-2 airplane. Results regarding an airplane with the flaps and gear retracted, airplane at sea level with flaps deflected 50 degrees and landing gear lowered, and effect of assumed modifications to airplane are provided.
Date: April 15, 1949
Creator: Queijo, M. J. & Michael, W. H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analytical and Experimental Investigation of 90 Degrees Supersonic Turning Passages Suitable for Supersonic Compressors or Turbines

Description: "Four 90 degree two-dimensional turning passages designed by the method of characteristics were tested at an inlet Mach number of 1.71. The measured losses varied from 5 to 15 percent of the inlet stagnation pressure. The smallest loss was obtained for a passage in which separation on the convex surface was minimized through the introduction of a favorable pressure gradient" (p. 1).
Date: September 12, 1949
Creator: Liccini, Luke L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analytical determination of effect of water injection on power output of turbine-propeller engine

Description: From Introduction: "Water injection at the compressor inlet has been successfully used to increase the thrust of turbojet engines. References 1 and 2 indicate that the sea-level static thrust of a centrifugal-flow-type turbojet engine may be increased about 25 percent by use of liquid injection. Reference 3 indicates that greater thrust augmentation is possible at a compressor pressure ratio of 11 than of 4."
Date: November 3, 1949
Creator: Ross, Albert O. & Huppert, Merle C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Approximate Method for Estimating the Incompressible Laminar Boundary-Layer Characteristics on a Flat Plate in Slipping Flow

Description: Memorandum presenting an approximate method for the estimation of the properties of the incompressible laminar boundary layer on a flat plate in the slip-flow region using Karman's momentum method. At equivalent stations, the total thickness and the skin friction of a slipping boundary layer are less than that of the normal boundary layer at the same Reynolds number.
Date: May 2, 1949
Creator: Donaldson, Coleman duP.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Bibliography of Classified Aircraft-Fire Literature

Description: Memorandum presenting a bibliography of unclassified aircraft fire literature consisting of reports from a 20-year period ending January 1, 1949. The reports are separated into the following categories: aircraft fire accidents and statistics, combustibles, ignition sources, fire protection, fire prevention, fire resistance of materials, fire detecting, fire extinguishing, and passenger protection or rescue.
Date: November 10, 1949
Creator: Weiss, Solomon & Pesman, Gerard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculation of Aerodynamic Forces on a Propeller in Pitch or Yaw

Description: Report presenting an analysis to determine the applicability of existing propeller theory and the theory of oscillating airfoils to the problem of determining the magnitude of the forces on propellers in pitch or yaw. The steady-state method for calculating propeller forces appears to give satisfactory results.
Date: February 15, 1949
Creator: Crigler, John L. & Gilman, Jean, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Calculative method for estimating the interference pressure field at zero lift on a symmetrical swept-back wing mounted on a circular cylindrical body

Description: Report presenting an approximate method for calculating the interference pressure distribution at zero lift of a symmetrical sweptback wing mounted on a circular cylindrical body with the chord plane of the wing passing through the axis of the body. An example is provided using a circular cylindrical body and an untapered wing with 60 degrees of sweepback.
Date: August 5, 1949
Creator: Nielsen, Jack N. & Matteson, Frederick H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Calibration Tests of a German Log Rodmeter

Description: A German log rodmeter of the pitot static type was calibrated in Langley tank no. 1 at speeds up to 34 knots and angles of yaw from 0 deg to plus or minus 10 3/4 degrees. The dynamic head approximated the theoretical head at 0 degrees yaw but decreased as the yaw was increased. The static head was negative and in general became more negative with increasing speed and yaw. Cavitation occurred at speeds above 31 knots at 0 deg yaw and 21 knots at 10 3/4 deg yaw.
Date: March 17, 1949
Creator: Mottard, Elmo J. & Stillman, Everette R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Calibration Tests of a Japanese Log Rodmeter

Description: A Japanese log rodmeter of the rotating-vane impeller type, with a commutator on the impeller shaft, was calibrated in Langley tank no. 1. The rotational speed of two impellers was determined for forward speeds up to 24 knots at angles of yaw up to ?10 0 . In general, the rotational speeds of two apparently identical impellers tested in the rodmeter decreased with increasing yaw angle, right yaw causing a greater decrease than left yaw. The difference in calibration between the two impellers wa… more
Date: March 9, 1949
Creator: Mottard, Elmo J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Carbon deposition from AN-F-58 fuels in a J33 single combustor

Description: Report presenting an investigation using a single combustor from a 4600-pound-thrust turbojet engine to determine the amount of carbon deposition of AN-F-58 fuels and the effect of carbon formations in the combustor on the altitude operational limits. Three fuel blends conforming to AN-F-58 specification were prepared in order to determine the influence of boiling temperature and of aromatic content on carbon deposition. Results regarding carbon deposition and effect of carbon formations on alt… more
Date: June 24, 1949
Creator: Wear, Jerrold D. & Douglass, Howard W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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