Search Results

open access

A 37,500 KW Power Reactor with Competitive Possibilities

Description: The following report follows the study on economics of nuclear power generation using a light water reactor.
Date: February 26, 1954
Creator: Thompson, W. I. & Cohen, Karl
Partner: UNT Libraries Government Documents Department
open access

Advanced Seminar in Reactor Physics

Description: The following report provides equations that result from a seminar in reactor physics.
Date: July 26, 1950
Creator: Smith, Nicholas M.
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic characteristics at high speeds of full-scale propellers having Clark Y blade sections

Description: From Introduction: "The single purpose of this paper is to make available the data obtained from tests of these two Clark Y section propellers as quickly as possible with no attempt being made to analyze the results or to compare them with other high-speed-propeller test results."
Date: October 26, 1948
Creator: Johnson, Peter J.
Partner: UNT Libraries Government Documents Department
open access

The Aerodynamic Characteristics of Airfoils at Negative Angles of Attack

Description: From Introduction: "The present report gives all the results, including those published in reference 1 and the results of previously un-published tests tests of the airfoils at positive angles of attack."
Date: February 26, 1932
Creator: Anderson, Raymond F.
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic characteristics of various configurations of a model of a 45 degree swept-wing airplane at a Mach number of 2.01

Description: An investigation has been conducted at the Langley 4- by 4-foot supersonic pressure tunnel at a Mach nmber of 2.01 to determine the aerodynamic characteristics of several configurations of a model of a 45 deg swept-wing airplane. The basic configuratin had a wing with 45 deg sweepback at the quarter-chord line, aspect ration 3.2, taper ration 0.468, NACA 65A005.5 sections just outboard of the inlet and NACA 65A003.7 sections at the tip. The wing was mounted slightly above the body center line and an all-movable horizantal tail was located slightly below the extended chord line of the wing. Tre design incorporated twin wing-root supersonic inlets ducted to a single exit at the base of the fuselage. The configurations investigated included an extended nose length, a bumped-fuselage afterbody, an inlet droop, an lncreased wing aspect ratio, and a revised canopy shape. Configurations employing the wing of increased aspect ratio of 3.7, which constituted the bulk of the tests, produced about a 10-percent increase in lift and in longitudinal stability as compared with the basic wing of aspect ratio 3.2. There was a slight but masurable increase in minimum drag and maximum lift-drag ratio.
Date: May 26, 1955
Creator: Spearman, M. Leroy; Driver, Cornelius & Robinson, Ross B.
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic heat transfer and zero-lift of a flat windshield canopy on the NACA RM-10 research vehicle at high Reynolds numbers for a flight Mach number range from 1.5 to 3.0

Description: Report presenting the aerodynamic heat-transfer properties and zero-lift drag of a typical pilot's canopy as determined by a rocket-model flight test through a range of Mach and Reynolds numbers. The canopy had a 63 degree sweptback flat windshield, circular cross section, and an equivalent body fineness ratio of 7.0. Results regarding the canopy temperature distribution, canopy pressure distribution, heat-transfer coefficient, and drag are provided.
Date: September 26, 1956
Creator: Hoffman, Sherwood & Chauvin, Leo T.
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Characteristics at a Mach number of 1.53 including effect of small variations of sweep

Description: Measured values of lift, drag, and pitching moment at a Mach number of 1.53 and Reynolds numbers of 0.31, 0.62, and 0.84 million are presented for a wing-fuselage combination having a wing leading-edge sweep angle of 63 degrees, an aspect ratio of 3.42, a taper ratio of 0.25, and an NACA 64A006 section in the stream direction. Data are also presented for sweep angles of 57.0 degrees, 60.4 degrees, 67.0 degrees, and 69.9 degrees. The experimentally determined characteristics were less favorable than indicated by the linear theory but the experimental and theoretical trends with sweep were in good agreement. Boundary-layer-flow tests showed that laminar boundary-layer separation was the primary cause of the differences between experiment and theory.
Date: January 26, 1949
Creator: Madden, Robert T.
Partner: UNT Libraries Government Documents Department
open access

Air-flow characteristics of brazed and rolled wire filter cloth for transpiration-cooled afterburners

Description: From Introduction: "Because of variation in the static-pressure drop across the porous material and in the cooling air required along the length of afterburner combustion chambers, a prescribed distribution of permeability is usually necessary. However, as a preliminary investigation, this report is concerned only with the attainment of uniform permeability. The results of an experimental investigation, conducted at the NACA Lewis laboratory, to determine the permeabilities of five thick meshes of wire filter cloth are presented herein."
Date: October 26, 1953
Creator: Koffel, William K.
Partner: UNT Libraries Government Documents Department
open access

Airborne Radiometric Survey of the East Flank of the Big Horn Mountains, Wyoming and Montana

Description: Abstract: An airborne radiometric survey of parts of the east flank of the Big Horn Mountains was begun on June 23, and completed on August 27, 1952. An area of approximately 250 square miles was covered, and only two anomalies were found in the entire area. Flight lines were arranged in accordance with the geology of the area, particular attention being given to formations the stratigraphic equivalents of which are known to be uranium bearing in other areas. Two additional zones of radioactivity were found by ground investigation, but assays from both the ground and the airborne discoveries showed no economic uranium deposits.
Date: September 26, 1952
Creator: Jones, E. E.
Partner: UNT Libraries Government Documents Department
open access

Altitude-Chamber Performance of British Rolls-Royce Nene II Engine 2: 18.41-Inch-Diameter Jet Nozzle

Description: Report presenting an altitude-chamber investigation to determine the altitude performance characteristics of the British Rolls-Royce Nene II turbojet engine with an 18.41-inch-diameter jet nozzles. Testing occurred at a range of simulated altitudes and ram-pressure ratios. Results regarding the simulated flight performance, generalized performance, and effect of jet-nozzle area on performance are provided.
Date: October 26, 1949
Creator: Armstrong, J. C.; Wilsted, H. D. & Vincent, K. R.
Partner: UNT Libraries Government Documents Department
open access

Altitude performance investigation of a high-temperature afterburner

Description: From Introduction: "In response to the ever-increasing need for high thrust augmentation, an investigation was conducted that had as its primary objective the attainment of maximum exhaust-gas temperature and thrust (ref. 1). The investigation reported herein was therefore conducted to ascertain the operational limits of the most promising high-temperature afterburner design of reference 1 and to determine its performance over a wind range of flight conditions."
Date: June 26, 1953
Creator: Huntley, S. C.; Auble, Carmon M. & Useller, James W.
Partner: UNT Libraries Government Documents Department
open access

Altitude Wind Tunnel Investigation of High-Temperature Afterburners

Description: From Introduction: "During previous investigations of afterburning conducted at the NACA Lewis laboratory (references 1 to 4, for example), the objective of obtaining high exhaust-gas temperatures and, consequently, maximum thrust augmentation was compromised to some extent in order to alleviate the problem of afterburner shell cooling. The primary objective of the investigation reported herein was therefore the attainment of maximum exhaust-gas temperature imposed by the cooling techniques previously used, a secondary flow of cooling air was provided around the afterburner shell."
Date: June 26, 1952
Creator: Conrad, E. William & Campbell, Carl E.
Partner: UNT Libraries Government Documents Department
open access

Altitude-Wind-Tunnel Investigation of Performance of Several Propellers on YP-47M Airplane at High Blade Loading 2 - Curtiss 838-1C2-18R1 Four-Blade Propeller

Description: "An investigation was conducted in the Cleveland altitude wind tunnel to determine the performance of a Curtiss propeller with four 838-1C2-1SR1 blades on a YP-47M airplane at high blade loadings and engine powers. The study was made for a range of power coefficients between 0.30 and 1.00 at free-stream Mach numbers of 0.40 and 0.50. The results of the force measurements indicate primarily the trend of propeller efficiency for changes in power coefficient or advance-diameter ratio, inasmuch as corrections for the effects of tunnel-wall constriction on the installation have not been applied" (p. 1).
Date: November 26, 1946
Creator: Wallner, Lewis E. & Sorin, Solomon M.
Partner: UNT Libraries Government Documents Department
open access

Altitude-Wind-Tunnel Investigation of Performance of Several Propellers on YP-47M Airplane at High Blade Loadings 4 - Curtiss 732-1C2-0 Four-Blade Propeller

Description: "An altitude-wind-tunnel investigation has been made to determine the performance of a Curtiss 732-1C2-0 four-blade propeller on a YP-47M airplane at high blade loadings and engine power. Propeller characteristics were obtained for a range of power coefficients from 0.30 to 1.00 at free-stream Mach numbers of 0.40 and .50" (p. 1).
Date: November 26, 1946
Creator: Saari, Martin J. & Sorin, Solomon M.
Partner: UNT Libraries Government Documents Department
open access

Analysis of effect of basic design variables on subsonic axial-flow-compressor performance

Description: From Summary: "A blade-element theory for axial-flow compressors has been developed and applied to the analysis of the effects of basic design variables such as Mach number, blade loading, and velocity distribution on compressor performance. The relations among several efficiencies useful in compressor design are derived and discussed. The possible gains in useful operating range obtainable by the use of adjustable stator blades are discussed and a rapid approximate method of calculating blade-angle resettings is shown by an example."
Date: November 26, 1947
Creator: Sinnette, John T., Jr.
Partner: UNT Libraries Government Documents Department
open access

Analysis of pressure data obtained at transonic speeds on a thin low-aspect-ratio cambered delta wing-body combination

Description: From Introduction: "Wind-tunnel and flight tests have shown that conical leading-edge camber on a thin low-aspect-ratio delta wing results in increasing the lift-drag ratio at transonic and low supersonic speeds (refs. 1 and 2). References 3 and 4 present the results of two previous investigations of this general program. A more detailed analysis of the pressure distributions of reference 5 is presented herein in terms of total section loads and overall wing-body characteristics."
Date: September 26, 1958
Creator: Mugler, John P., Jr.
Partner: UNT Libraries Government Documents Department
open access

Analysis of some parameters used in correlating blowing-type boundary-layer control data

Description: Report presenting an examination of the limitations of the use of jet momentum coefficient as a correlating factor in comparing tests of blowing-type boundary-layer control. Theoretical and experimental data indicate that it should be an acceptable parameter where the duct pressures are large.
Date: September 26, 1956
Creator: Kelly, Mark W.
Partner: UNT Libraries Government Documents Department
open access

Analysis of the turbojet engine for propulsion of supersonic fighter airplanes

Description: An analytical investigation was made of two supersonic interceptor type airplanes to determine the most desirable turbojet engine characteristics for this application The airplanes were designed differently primarily because of the amount of subsonic flight incorporated in the flight plan--one flight having none and the other, a cruise radius of 400 nautical miles. Several power plant design variables were varied independently to determine the effect of changes in each parameter on airplane performance. These parameters included compressor pressure ratio, compressor efficiency, turbine-inlet temperature, afterburner temperature, engine specific weight, and air-handling capacity. The effects of using a convergent-divergent exhaust nozzle and of changing the design flight Mach number were also investigated.
Date: October 26, 1953
Creator: Gabriel, David S.; Krebs, Richard P.; Wilcox, E. Clinton & Koutz, Stanley L.
Partner: UNT Libraries Government Documents Department
open access

Analytical Chemistry Division Quarterly Progress Report for Period Ending September 10, 1951

Description: Technical report covering experiments happening on the Analytical Chemistry Division's sites at the Oak Ridge National Laboratory. Includes information on ionic analyses, radio-chemical analyses, spectrochemical analyses, service analyses, inorganic preparations, analytical chemical control of homogeneous reactor solution, optical and electron microscopy, and service analyses for the period ending September 10, 1951. Studies and happenings took place on the Analytical Chemistry Division's X-10 and Y-12 sites. [From Table of Contents, Abstract]
Date: February 26, 1952
Creator: Kelley, M. T. & Susano, C. D.
Partner: UNT Libraries Government Documents Department
open access

Analytical Investigation of Fuel-Cooled Turbine Blades With Return-Flow Type of Finned Coolant Passages

Description: Memorandum presenting an investigation of coolant-flow rates for a turbine rotor blade with return-flow type of coolant-passage configuration formed by fins within a capped blade shell with both hydrogen and methane fuels as coolants. Results regarding spanwise blade and coolant temperature distributions, effects of coolant inlet temperature on hydrogen-coolant-flow requirements, comparison of return-flow-blade coolant requirements, effect of fin thickness and fin height, comparison of hydrogen and methane as coolants, and feasibility of fuel-cooled turbines are provided.
Date: June 26, 1957
Creator: Nachtigall, Alfred J. & Slone, Henry O.
Partner: UNT Libraries Government Documents Department
open access

Analytical investigation of fuel-cooled turbine blades with return-flow type of finned coolant passages

Description: From Introduction: "The purpose of this report was to investigate the possible use of engine fuels (hydrogen and methane) as coolants for turbine rotor blades and to determine the pressure-drop characteristics of these coolants for a turbine blade with a more effective coolant-passage configuration than that considered in reference 5 but for the same engine and flight conditions."
Date: June 26, 1957
Creator: Nachtigall, Alfred J. & Slone, Henry O.
Partner: UNT Libraries Government Documents Department
open access

Application of Theodorsen's Theory to Propeller Design

Description: "A theoretical analysis is presented for obtaining by use of Theodorsen's propeller theory the load distribution along a propeller radius to give the optimum propeller efficiency for any design condition. Examples are included to illustrate the method of obtaining the optimum load distributions for both single-rotating and dual-rotating propellers" (p. 1).
Date: July 26, 1948
Creator: Crigler, John L.
Partner: UNT Libraries Government Documents Department
open access

APPR-1 Research and Development Program. Design Analysis for Flow and Temperature Measurement Program, Task No. 5

Description: From objectives: "To establish, by literature search, analysis and design, the engineering and fabrication requirements for modifying reactor components and developing and installing the necessary instrumentation to carry out a fuel temperature and flow measurement experimental program."
Date: September 26, 1958
Creator: Richards, W. M. S.
Partner: UNT Libraries Government Documents Department
Back to Top of Screen