UNT Libraries Government Documents Department - 55 Matching Results

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Altitude Investigation of Several Afterburner Configurations for the J40-WE-8 Turbojet Engine

Description: "An investigation was conducted in the Lewis altitude wind tunnel to evaluate the performance and operational characteristics of the J40-WE-8 afterburner. A brief program of minor modifications to the flame holder, diffuser, and fuel system was undertaken to improve at a burner-inlet pressure level of 620 pounds per square foot. At this pressure level, modifications to the fuel system resulted in an increase in maximum net thrust from 1500 to 1600 pounds and a reduction in specific fuel consump… more
Date: July 16, 1953
Creator: Conrad, E. William & Campbell, Carl E.
Item Type: Refine your search to only Report
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Burning rates of single fuel drops and their application to turbojet combustion process

Description: Report presenting burning rates for single isooctane drops suspended in various quiescent oxygen-nitrogen atmospheres at room temperature and pressure. The burning rates were compared with those predicted by a previously developed theory based on a heat- and mass-transfer mechanism and with values predicted by a modification to the theory.
Date: July 16, 1953
Creator: Graves, Charles C.
Item Type: Refine your search to only Report
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Comparative Tensile Strengths at 1200 Degrees F of Various Root Designs for Cermet Turbine Blades

Description: Report presenting specimens of five different root designs, proportioned in accordance with the design surveys, and specimens of a conventional fir-tree turbine root were fabricated from a titanium carbide cement bonded with nickel. Comparative strengths were determined by short-term tensile tests at 1200 degree Fahrenheit. Results regarding blade root evaluation and rotor-segment evaluation are provided.
Date: June 16, 1953
Creator: Meyer, André J., Jr.; Kaufman, Albert & Calvert, Howard F.
Item Type: Refine your search to only Report
open access

Comparison of ignition delays of several propellant combinations obtained with modified open-cup and small-scale rocket engine apparatus

Description: From Summary: "Ignition delays of several propellant combinations obtained with a modified open-cup apparatus and with a small-scale rocket engine of approximately 50-pounds thrust were compared to study any correlations that might exist between the two methods of ignition-delay determination. The results were used in determining the relative utility of each apparatus."
Date: June 16, 1953
Creator: Ladanyi, Dezso J. & Miller, Riley O.
Item Type: Refine your search to only Report
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Comparison of theoretical and experimental zero-lift drag-rise characteristics of wing-body-tail combinations near the speed of sound

Description: Report presenting the zero-lift drag rise at low supersonic speeds computed by linearized theory for several wing-body-tail combinations and a comparison with experimental data. The results indicate that the computation method is capable of computing the drag rise at low supersonic speeds to an accuracy of about 20 percent.
Date: October 16, 1953
Creator: Holdaway, George H.
Item Type: Refine your search to only Report
open access

The Determination of Cu-64 in Reactor Effluent Water by Electrodeposition

Description: An analytical method for Cu-64 in reactor effluent has been studied based upon electrodeposition of the active copper with inert copper carrier. A two hour plating time was employed at a current density of 10 ma/sq cm and four volts across the cell. A stainless steel cathode plate was used. Carrier yields of greater than 80% were obtained with a standard deviation of the yield-corrected counting rate as low as 0.24%. Very little, if any contamination by other radioactive elements present wa… more
Date: September 16, 1953
Creator: Perkins, R. W. (Richard W.)
Item Type: Refine your search to only Report
open access

Determination of Zirconium and Total Fluoride Ion in Zirconium - Hydrofluoric Acid Solutions

Description: An analytical method has been developed for zirconium and fluoride ions in the system resulting from the dissolution of fuel elements in hydrofluoric acid. The method is based on determination of the density and electrical conductivity of the dissolved metal solution.
Date: February 16, 1953
Creator: Vogler, Seymour; Vogel, Richard C. & Shor, R. W. (Roberta W.)
Item Type: Refine your search to only Report
open access

Effect of Boron Liner on Neutron Background in Cavity

Description: Introduction: "In connection with conducting neutron experiments in a pit with earth and concrete walls, it was proposed that the background flux of neutrons might be reduced by lining the walls of the pit with a neutron absorber such as boron. To determine how much liner material would be desirable and what diminution in the neutron background could be expected, the following measurements were undertaken."
Date: January 16, 1953
Creator: Benveniste, Jack
Item Type: Refine your search to only Report
open access

Effect of Engine and Control Limits on Steady-State and Transient Performance of Turbojet Engine With Variable-Area Exhaust Nozzle

Description: Memorandum presenting steady-state and transient characteristics of the J34-WE-32 turbojet engine with electronic power regulator as obtained in the altitude wind tunnel to determine the effects of engine and control limits on the performance. Limits on the fuel valve and exhaust nozzle area influence any schedule of speed and temperature. Results regarding the effect of limits on operating schedule, effect of altitude on safe operating range, effect of minimum fuel flow settings on transient p… more
Date: January 16, 1953
Creator: Vasu, George & Hinde, William L.
Item Type: Refine your search to only Report
open access

The Effects of Extensible Rocket Racks on Lift, Drag, and Stability of a 1/10 Scale Rocket-Boosted Model of the McDonnell XF3H-1 Airplane for a Mach Number Range of 0.60 to 1.34

Description: Report presenting testing of the transonic longitudinal characteristics of a model of the McDonnell XF3H-1 airplane. The model had a center-of-gravity location of 28.5 percent of the mean aerodynamic chord and a stabilizer setting of -5.91 degrees relative to the wing chord plane with extensible rocket racks. Results regarding Reynolds number, rocket-rack program, flight time history, trim, lift, drag, longitudinal stability, directional stability, and inlet pressure recovery are provided.
Date: June 16, 1953
Creator: Crabill, Norman L.
Item Type: Refine your search to only Report
open access

The Effects of Extensible Rocket Racks on Lift, Drag, and Stability of a 1/10-Scale Rocket-Boosted Model of the McDonnell XF3H-1 Airplane for a Mach Number Range of 0.60 to 1.34 : TED No. NACA DE 31

Description: Memorandum presenting the results of a test on the transonic longitudinal characteristics of a scale rocket model of the McDonnell XF3H-1 airplane. The model, flown with a center-of-gravity location of 28.5 percent of the mean aerodynamic chord and a stabilizer setting of -5.91 degrees relative to the wing chord plane, was equipped with extensible rocket racks. Results regarding the Reynolds number, rocket-rack program, flight time history, trim, lift, drag, longitudinal stability, directional … more
Date: June 16, 1953
Creator: Crabill, Norman L.
Item Type: Refine your search to only Report
open access

Evaporation and Spreading of Isooctane Sprays in High Velocity Air Streams

Description: Memorandum presenting an investigation of the evaporation and spreading of isooctane sprays over a range of inlet-air conditions common in ram-jet engines. The total and liquid fuel distribution across the duct were determined. Over the specified ranges in the investigation, expressions were obtained which related the evaporation rate and degree of spreading of the sprays to the experimental variables.
Date: November 16, 1953
Creator: Bahr, Donald W.
Item Type: Refine your search to only Report
open access

Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine 13: Endurance Evaluation of Several Protective Coatings Applied to Turbine Blades of Nonstrategic Steels

Description: Memorandum presenting an investigation of the durabilities of several protective coatings applied to air-cooled gas turbine rotor blades of nonstrategic steels in modified turbojet engines. Four types of coatings (ceramic, nickel, Nicrobraz, and aluminized) were applied to a total of 20 blades.
Date: July 16, 1953
Creator: Bartoo, Edward R. & Clure, John L.
Item Type: Refine your search to only Report
open access

Experimental Investigation of the Aerodynamic Characteristics of an Air-to-Air Missile Employing Cruciform Wings and Tail of Rectangular Plan Form at Mach Numbers of 1.4 and 1.9

Description: Memorandum presenting the aerodynamic characteristics of a model of an air-to-air missile employing variable-incidence cruciform wings of rectangular plan form and a fixed cruciform tail of rectangular plan form, an the characteristics of its body-wing and body-tail components, as determined from a wind-tunnel investigation for Mach numbers of 1.4 and 1.9. The results include normal-force, pitching-moment, and axial-force data for the body-wing-tail, body-wing, and body-tail combinations, and n… more
Date: February 16, 1953
Creator: Mead, Merrill H.
Item Type: Refine your search to only Report
open access

The Fabrication of Thorium Tubes

Description: Abstract: "Thorium tubes were cold drawn from extruded tube stock and also from drilled hot-rolled rod. Total reductions up to approximately 85 per cent were accomplished by conventional tube-drawing methods, without an intermediate anneal. The hard-drawn tubes had high tensile strength, but the ductility, as indicated by flaring and flattening tests, was low."
Date: January 16, 1953
Creator: Saller, Henry A. & Keeler, J. R.
Item Type: Refine your search to only Report
open access

Flight Investigation of Nine Reduced-Scale (1:3.75) Hermes A-2S Rocket-Motor Test Vehicles

Description: Tests were made to determine the motor performance characteristics under flight conditions at propellant preignition temperatures of -25 degrees F, ambient temperature, and 130 degrees F. Results regarding the trajectories of the various test vehicles, time histories of velocity and Mach number, acceleration time histories, thrust curves, and maximum variation of total impulse are provided.
Date: September 16, 1953
Creator: Falanga, Ralph A.
Item Type: Refine your search to only Report
open access

Free-Jet Investigation of a 20-Inch Ram-Jet Combustor Utilizing High-Heat-Release Pilot Burner

Description: Report presenting an investigation of the performance of a 20-inch-diameter ramjet engine with a high-heat-release pilot burner conducted at zero angle of attack in a free-jet test facility at a Mach number of 3.0. Two flame-holder configurations were used in conjunction with the high-heat-release pilot burner over a range of altitudes. Results regarding the performance of the high-heat-release pilot burner and performance of combustion-chamber configurations are provided.
Date: October 16, 1953
Creator: Henzel, James G., Jr. & Wentworth, Carl B.
Item Type: Refine your search to only Report
open access

Investigation of a Chromium Plus Aluminum Oxide Metal-Ceramic Body for Possible Gas Turbine Blade Application

Description: "A metal-ceramic composition containing approximately 80 percent chromium plus 20 percent aluminum oxide (Al(sub 2)O(sub 3)) by weight has been investigated for possible gas-turbine blade use. The results of modulus-of-rupture, thermal-shock, and blade-performance studies indicate that this material may have adequate thermal-shock resistance; however, the strength for the application appears marginal" (p. 1).
Date: November 16, 1953
Creator: Hoffman, Charles A.
Item Type: Refine your search to only Report
open access

Investigation of distribution of losses in a conservatively designed turbine

Description: "A primary objective of turbine research is to obtain information that will aid in the design of gas turbines for any given application with minimum losses. As part of a program to obtain such information, flow surveys downstream of both the stator and the rotor of an experimental turbine were made in order to obtain detailed information about the flow conditions and the losses within the machine. The single-stage, low-radius-ratio turbine studied is relatively conservative in design, having lo… more
Date: March 16, 1953
Creator: Whitney, Rose L.; Heller, Jack A. & Hauser, Cavour H.
Item Type: Refine your search to only Report
open access

Investigation of the Attenuation of Plane Shock Waves Moving Over Very Rough Surfaces

Description: "Experimental measurements of the attenuation of plane shock waves moving over rough walls have been made in a shock tube. Measurements of the boundary-layer characteristics, including thickness and velocity distribution behind the shock, have also been made with the aid of new cal techniques which provide direct information on the local boundary-layer conditions at the rough walls. Measurements of shock speed and shock pressure ratio are presented for both smooth-wall and rough-wall flow over … more
Date: June 16, 1953
Creator: Huber, Paul W.; McFarland, Donald R. & Levine, Philip
Item Type: Refine your search to only Report
open access

An investigation of the effects of heat transfer on boundary-layer transition on a parabolic body of revolution (NACA RM-10) at a Mach number of 1.61

Description: Report presents the results of an investigation conducted to determine the effects of heat transfer on boundary-layer transition on a parabolic body of revolution (NACA rm-10 without fins) at Mach number of 1.61 and over a Reynolds number range from 2.5 x 10(6) to 35 x 10(6). The maximum cooling of the model used in these tests corresponded to a temperature ratio (ratio of model-surface temperature to free-stream temperature) of 1.12, a value somewhat higher than the theoretical value required … more
Date: February 16, 1953
Creator: Czarnecki, K. R. & Sinclair, Archibald R.
Item Type: Refine your search to only Report
open access

Jet effects on flow over afterbodies in supersonic stream

Description: From Summary: "Current NACA research on the subject of jet effects on the flow over afterbodies in a supersonic stream is briefly summarized. Several jet nozzle types installed in various afterbody configurations are considered for a wide range of operating conditions."
Date: November 16, 1953
Creator: Cortright, Edgar M., Jr. & Kochendorfer, Fred D.
Item Type: Refine your search to only Report
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