Technical Report Archive & Image Library (TRAIL) - 308 Matching Results

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Aerodynamic characteristics of a wing with quarter-chord line swept back 35 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section: Transonic-bump method

Description: From Introduction: "This paper presents the results of the investigation of wing-alone and wing-fuselage combinations employing a wing with the quarter-chord line swept back 35^o, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section."
Date: April 21, 1949
Creator: Sleeman, William C., Jr. & Becht, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics of a wing with unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section

Description: From Introduction: "This paper presents the results of the investigation of the wing-alone and of the wing-fuselage configuration employing a wing with an unswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the air stream. The results of closely related sweptback-wing investigations, which are part of the present transonic programs, are presented in references 1 to 3."
Date: October 21, 1949
Creator: Goodson, Kenneth W. & Morrison, William D., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics of NACA RM-10 missile in 8- by 6-foot supersonic wind tunnel at Mach numbers from 1.49 to 1.98 2: presentation and analysis of force measurements

Description: Experimental investigation of aerodynamic forces acting on body of revolution (NACA RM-10 missile) with and without stabilizing fins was conducted at Mach numbers from 1.49 to 1.98 at angles of attack from 0 to 9 degrees and at Reynolds number of approximately 30,000,000. Comparison of experimental lift, drag, and pitching-moment coefficients and center of pressure location for body alone is made with linearized potential theory and a semiempirical method. Results indicate that aerodynamic char… more
Date: July 21, 1950
Creator: Esenwein, Fred T.; Obery, Leonard J. & Schueller, Carl F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: Investigation of a large-scale model at low speed

Description: From Introduction: "This report presents the aerodynamic characteristics at low speed end high Reynolds number as determined in the Ames 40- by 80 foot wind tunnel."
Date: January 21, 1949
Creator: McCormack, Gerald M. & Walling, Walter C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Air-Core Strong Focusing Synchrotron

Description: The following report is based on work performed under the auspices of the U.S. Atomic Energy Commission. The purpose of this report is to describe an air-core strong focusing synchrotron and its functions.
Date: August 21, 1959
Creator: Christofilos, Nicholas C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department

Airborne radioactivity survey of portions of the Defiance Uplift and Carrizo Mountains, Apache County, Arizona

Description: Aerial image shows the result of an airborne radioactive survey over an area of 940 square miles in Apache County, Arizona with the approximate location of radioactivity anomalies found. Text describes methods used and discusses the anomalies.
Date: June 21, 1953
Creator: Moxham, Robert Morgan & Johnson, R. W.
Item Type: Refine your search to only Map
Partner: UNT Libraries Government Documents Department
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Altitude Starting Tests of a Small Solid Propellant Rocket

Description: From Summary: "Four solid-propellant rocket engines of nominal 500-pound thrust were tested for starting characteristics at pressure altitudes ranging from 89,000 to 111,000 feet and at a temperature of -75^o F. Chamber pressures were measured on two of the runs. Average chamber pressures in these two runs were lower than expected, although action times agreed with the expected values."
Date: June 21, 1957
Creator: Sloop, John L. & Krawczonek, Eugene M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude Wind Tunnel Investigation of the Performance of Compressor, Combustor, and Turbine Components of Prototype J47D (RX1-1) Turbojet Engine

Description: "As a portion of an over-all performance investigation of the prototype J47D (RX-1) turbojet engine, performance of the compressor, combustor, and turbine components has been determined in the Lewis altitude wind tunnel over a range of altitude from 5000 to 55,000 feet and at flight Mach numbers from 0.19 to 0.92. Investigations were conducted with the engine operating on an electronic control schedule and slow with a two-lever control system by which fuel flow and exhaust-nozzle area could be … more
Date: December 21, 1951
Creator: Farley, John M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Altitude-Wind-Tunnel Investigation of Turbine Performance in J47 Turbojet Engine

Description: From Introduction: "Performance data are presented in this report to show the characteristics of the turbine operating as an integral part of the engine. Typical results are graphically presented to show the effects of changes in altitude, flight Mach number, and exhaust-nozzle-outlet area on turbine performance. All turbine-performance data obtained are given in tabular form."
Date: September 21, 1950
Creator: Thorman, H. Carl & McAulay, John E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of a Pneumatic Probe for Measuring Exhaust-Gas Temperatures with Some Preliminary Experimental Results

Description: "A pneumatic probe based on continuity of mass flow through two restrictions separated by a cooling chamber was constructed to measure gas temperature at and beyond the limit of thermocouples. This probe consisted of a subsonic flat-plate orifice for the first restriction and a sonic-flow converging-diverging nozzle for the second restriction. The effect of variation in gas constants on the calibration is examined for common engine-exhaust gases" (p. 1).
Date: May 21, 1952
Creator: Scadron, Marvin D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of Factors Affecting Selection and Design of Air-Cooled Single-Stage Turbines for Turbojet Engines 2: Analytical Techniques

Description: Memorandum presenting computation methods for analyzing turbojet-engine performance for a series of air-cooled nonafterburning and afterburning engines where all the engine components are simultaneously aerodynamically limited. The coolant-flow ratio was arbitrarily assigned so that the results of the analysis can be applied to any specific air-cooled blade configurations.
Date: June 21, 1954
Creator: Rossbach, Richard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of Heat and Compressibility Effects in Internal Flow Systems and High-Speed Tests of a Ram-Jet System

Description: Report discussing an analysis has been made by the NACA of the effects of heat and compressibility in the flow through the internal systems of aircraft along with equations and charts are developed whereby the flow characteristics at key stations in a typical internal system may be readily obtained.
Date: July 21, 1942
Creator: Becker, John V. & Baals, Donald D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An analysis of once-per-revolution oscillating aerodynamic thrust loads on single-rotation propellers on tractor airplanes at zero yaw

Description: A simplified procedure is shown for calculating the once-per-revolution oscillating aerodynamic thrust loads on propellers of tractor airplanes at zero yaw. The only flow field information required for the application of the procedure is a knowledge of the upflow angles at the horizontal center line of the propeller disk. Methods are presented whereby these angles may be computed without recourse to experimental survey of the flow field. The loads computed by the simplified procedure are compar… more
Date: March 21, 1955
Creator: Rogallo, Vernon L.; Yaggy, Paul F. & McCloud, John L., III
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Analysis of Pressure Studies and Experimental and Theoretical Downwash and Sidewash Behind Five Pointed-Tip Wings at Supersonic Speeds

Description: The following report covers an investigation that was done to supplement available experimental data on flow fields behind wings of an aircraft at supersonic speeds, as well as to furnish more quantitative information on the choice of the theoretical method for a given configuration and the accuracy to be expected when using such a method.
Date: April 21, 1954
Creator: Boatright, William B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An analysis of surface pressures and aerodynamic load distribution over the swept wing of the Douglas D-558-II research airplane at Mach numbers from 0.73 to 1.73

Description: Report presenting the wing-section pressure-distribution and wing-panel load characteristics of the Douglas D-558-II airplane for a range of Mach numbers and airplane normal-force coefficients. At subsonic speeds, the pressure distributions are characterized by a high negative-pressure peak with an abrupt pressure recovery as a result of the leading-edge expansion over the upper surface at moderate angles of attack.
Date: April 21, 1958
Creator: Taillon, Norman V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analytical and experimental study of transient-response characteristics of a turboprop engine

Description: From Introduction: "The objectives of this report are to present methods and information sufficient for a lineralized dynamic description of the significant dependent and independent variables of a turboprop engine."
Date: October 21, 1955
Creator: Craig, R. T.; Nakanishi, S. & Wile, D. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Analytical Evaluation of the Effects of an Aerodynamic Modification and of Stability Augmenters on the Pitch Behavior and Probable Pilot Opinion of Two Current Fighter Airplanes

Description: Memorandum presenting the effects of wing modification and stability augmentation on the computed longitudinal behavior in the pitch-up region and probable pilot opinion of the pitch-up characteristics of two current fighter airplanes. An exploration of the addition of a wing-leading edge is included. Results regarding computed pitch-up behavior and probable pilot opinion are provided.
Date: April 21, 1959
Creator: Sadoff, Melvin & Stewart, John D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Anisotropic Elastic Scattering of Neutrons

Description: In an elastic collision the neutron loses part of its kinetic energy to the nucleus with both the kinetic and momentum of the system being conserved. However, for many elements the scattering is not isotropic in the center-of-mass system at the higher neutron energies. Many of the present reactor multigroup codes include anisotropic scattering at the high neutron energies, while many others assume isotropic scattering at all energies. In order to consider some of the effects of including anisot… more
Date: March 21, 1957
Creator: Copenhaver, C. M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Application of the Analogy Between Water Flow With a Free Surface and Two-Dimensional Compressible Gas Flow

Description: "The theory of the hydraulic analogy -- that is, the analogy between water flow with a free surface and two-dimensional compressible gas flow -- and the limitations and conditions of the analogy are discussed. A test was run using the hydraulic analogy as applied to the flow about circular cylinders of various diameters at subsonic velocities extending into the supercritical range. The apparatus and techniques used in this application are described and criticized" (p. 311).
Date: August 21, 1946
Creator: Orlin, W. James; Lindner, Norman J. & Bitterly, Jack G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Aqua Recia Flowsheet for Uranium Dissolution

Description: Relatively long time cycles are required for the standard nitric acid dissolution of enriched uranium using safe batch size techniques for criticality control. Upwards of forty eight hours are required for the total dissolution of solid of I and E enriched slugs in nitric acid. The dissolution capacity may be increased by: (1) using a dissolver critically safe by virtue of its geometry or, (2)increasing the rate of uranium dissolution. Dilute agua regia -- a mixture of hydrochloric and nitric a… more
Date: July 21, 1959
Creator: Shefcik, J. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Argonne National Laboratory Biology Division Quarterly Report: August to October, 1946

Description: From introductory paragraph: "This is the first quarterly report of the Biology Division of the Argonne National Laboratory. During the three-month period covered by this report, a large share of the time of many investigators has been spent in collating work done under the Biology Section of the Metallurgical laboratory for publication in the Plutonium Project Record. The large amount of work done under wartime pressure has made this, as in other divisions and projects, an important part of th… more
Date: November 21, 1946
Creator: Bruss, Austin M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Basic Magnetic Quantities and the Measurement of the Magnetic Properties of Materials

Description: From Introduction: "The work of the Magnetic Measurements Section of the National Bureau of Standards includes (1) testing of specifically prepared test specimens intended for use as standards for checking magnetic testing apparatus (2) investigation and development of magnetic testing apparatus (3) calibration of mutual inductors, test coils, and instruments for measuring magnetic fields, and (4) investigations in the field of magnetics such as studies of phenomena associated with nuclear magn… more
Date: May 21, 1962
Creator: Sanford, Raymond L. & Cooter, Irvin L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Basic performance characteristics of several subsonic-diffuser-bypass-duct combinations for use with supersonic inlets

Description: Report presenting the basic performance characteristics of several types of designs of subsonic-diffuser-bypass-duct combinations for bypass flows up to one-third of the total flow. The tested bypass-duct design procedure was found to be greatly oversimplified and was unable to produce satisfactory performance because of the extreme adverse pressure gradient.
Date: January 21, 1957
Creator: Wood, Charles C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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