UNT Libraries Government Documents Department - 90 Matching Results

Search Results

Results: 1 - 24 next
open access

Aerodynamic Characteristics of Four Republic Airfoil Sections from Tests in Langley Two-Dimensional Low-Turbulence Tunnels

Description: "Four airfoils sections, designed by the Republic Aviation Corporation for the root and tip sections of the XF-12 airplane, were tested in the Langley two-dimensional low-turbulence tunnels to obtain their aerodynamic characteristics. Lift characteristics were obtained at Reynolds numbers of 3,000,000, 6,000,000, 9,000,000, and 14,000,000, whereas drag characteristics were obtained at Reynolds numbers of 3,000,000, 6,000,000, and 9,000,000. Pressure distributions were obtained for one of the ro… more
Date: September 27, 1945
Creator: Klein, Milton M.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics of Several NACA Airfoil Sections at Seven Reynolds Numbers From 0.7 X 10(Exp 6) to 9.0 X 10(Exp 6)

Description: Report presenting an investigation of the two-dimensional aerodynamic characteristics of several NACA airfoil sections at four Reynolds numbers. Results regarding the minimum drag, maximum lift, lift-curve slope, and angle of zero lift and pitching moment are provided.
Date: May 27, 1948
Creator: Loftin, Laurence K., Jr. & Poteat, M. Irene
Item Type: Refine your search to only Report
open access

Allowable temperature rise in tubes of the piles: Precautions against boiling

Description: In the design of the pile, it was considered advisable never to impose so great a heat load on any tube that the available header pressure would be insufficient to sweep the tube free of vapor if boiling should accidentally be initiated in the tube. Figures are given for the maximum temperature rises permissible, as function of header pressure and orifice diameter.
Date: September 27, 1945
Creator: Woods, W. K.
Item Type: Refine your search to only Report
open access

Bending and shear stresses developed by the instantaneous arrest of the root of a moving cantilever beam

Description: A theoretical and experimental investigation has been made of the behavior of a cantilever beam in transverse motion when its root is suddenly brought to rest. Equations are given for determining the stresses, the deflections, and the accelerations that arise in the beam as a result of the impact. The theoretical equations, which have been confirmed experimentally, reveal that, at a given percentage of the distance from root to tip, the bending stresses for a particular mode are independent of … more
Date: September 27, 1944
Creator: Stowell, Elbridge Z.; Schwartz, Edward B. & Houbolt, John C.
Item Type: Refine your search to only Report
open access

Bending of Rectangular Plates With Large Deflections

Description: "The solution of Von Karman's fundamental equations for large deflections of plates is presented for the case of a simply supported rectangular plate under combined edge compression and lateral loading. Numerical solutions are given for square plates and for rectangular plates with a width-span ratio of 3:1. The effective widths under edge compression are compared with effective widths according to Von Karman, Bengston, Marguerre, and Cox and with experimental results by Ramberg, Mcpherson, and… more
Date: May 27, 1941
Creator: Levy, Samuel
Item Type: Refine your search to only Report
open access

Calculated Condenser Performance for a Mercury-Turbine Power Plant for Aircraft

Description: "As part of an investigation of the application of nuclear energy to various types of power plants for aircraft, calculations have been made to determine the effect of several operating conditions on the performance of condensers for mercury-turbine power plants. The analysis covered 8 range of turbine-outlet pressures from 1 to 200 pounds per square inch absolute, turbine-inlet pressures from 300 to 700 pounds per square inch absolute,and a range of condenser cooling-air pressure drops, airpla… more
Date: August 27, 1948
Creator: Doyle, Ronald B.
Item Type: Refine your search to only Report
open access

A Case of Rod Warping

Description: Warping of a rod by a variation in heat transfer coefficient around the periphery is considered. Estimates for some simple cases are given, and a more precise numerical calculation is carried out in ne instance.
Date: May 27, 1944
Creator: Murray, F. & Young, Gale Jay
Item Type: Refine your search to only Report
open access

Characteristics of a Hot Jet Discharged from a Jet-Propulsion Engine

Description: From Summary: "An investigation of a heated jet was conducted in conjunction with tests of an axial-flow jet-propulsion engine in the Cleveland altitude wind tunnel. Pressure and temperature surveys were made across the jet 10 and 15 feet behind the jet-nozzle outlet of the engine. Surveys were obtained at pressure altitudes of 10,000, 20,000, 30,000, and 40,000 feet with test-section velocities from 30 to 110 feet per second and test-section temperatures from 60 F to -50 F. From measurements t… more
Date: December 27, 1946
Creator: Fleming, William A.
Item Type: Refine your search to only Report
open access

A Comparison of Flight Measurements With Calculations of the Loss in Rolling Effectiveness Due to Wing Twist

Description: "A flight investigation was conducted with a fighter-type airplane to determine the loss in rolling effectiveness due to wing twist, and the results are compared with the loss in rolling effectiveness calculated by use of a simplified method. The computed rolling velocities showed good agreement with experimentally determined rolling velocities throughout the Mach number range covered by the flights. Extrapolation of the flight data indicated a Mach number for reversal which agreed well with th… more
Date: August 27, 1948
Creator: Cooney, T. V. & Wollner, Bertram C.
Item Type: Refine your search to only Report
open access

Correlation of pressure drop data isothermal flow through standard process tube assembly

Description: The experimental data presented in HDC-1255 for the pressure drops through the various portions of a standard process tube assembly for isothermal flow are correlated in this report. Data include orifice sizes up to 0.310 inches. The equations have been adapted for the calculation of pressure drops or flow rates for clean tubes in pile operation. A systematic procedure is outlined for determining the pressure drops through each portion of the tube assembly. A method is presented for calculating… more
Date: December 27, 1949
Creator: Sege, C. A.
Item Type: Refine your search to only Report
open access

The Diffusion Length of Thermal Neutrons in Uranium

Description: Measurements made in a uranium cylinder result in a mean value of 1.55 cm. for the diffusion length L for distances of 1 to 4 cm. from the base of the cylinder. Calculations give a value which agrees with the experimental result and show further that L increases from 1.40 to 1.63 cm. as the neutrons diffuse a distance of 5 cm. into the uranium.
Date: May 27, 1944
Creator: Hughes, Donald James, 1915-1960 & Bragdon, E. W.
Item Type: Refine your search to only Report
open access

Dynamics of a turbojet engine considered as a quasi-static system

Description: From Summary: "A determination of the dynamic characteristics of a typical turbojet engine with a centrifugal compressor, a sonic-flow turbine-nozzle diaphragm, and fixed area exhaust nozzle is presented. A generalized equation for transient behavior of the engine was developed; this equation was then verified by calculations using compressor and turbine performance charts extrapolated from equilibrium operating data and by experimental data obtained from an engine operated under transients in … more
Date: July 27, 1949
Creator: Otto, Edward W. & Taylor, Burt L., III
Item Type: Refine your search to only Report
open access

The effect of high solidity on propeller characteristics at high forward speeds from wind-tunnel tests of the NACA 4-(3)(06.3)-06 and NACA 4-(3)(06.4)-09 two-blade propellers

Description: From Summary: "Tests of two-blade propellers having the NACA 4-(3)(06.3)-06 and NACA 4-(3)(06.4)-09 blade designs (blade activity factors of 179 and 263, respectively) have been made in the Langley 8-foot high-speed tunnel through a range of blade angle from 20 degrees to 70 degrees for free-stream Mach numbers from 0.165 to 0.725 to determine the effects of high solidity and compressibility on propeller characteristics. The tests are part of a general investigation of propellers at high forwar… more
Date: February 27, 1947
Creator: Delano, James B.
Item Type: Refine your search to only Report
open access

Effect of Maximum Cruise-Power Operation at Ultra-Lean Mixture and Increased Spark Advance on the Mechanical Condition of Cylinder Components

Description: "A continuous 50-hour test was conducted to determine the effect of maximum cruise-power operation at ultra-lean fuel-air mixture and increased spark advance on the mechanical conditions of cylinder components. The test was conducted on a nine-cylinder air-cooled radial engine at the following conditions:brake horsepower, 750; engine speed, 1900 rpm; brake mean effective pressure, 172 pounds per square inch; fuel-air ratio, 0.052; spark advance, 30 deg B.T.C.; and maximum rear-spark-plug-bushin… more
Date: September 27, 1945
Creator: Harris, Herbert B.; Duffy, Robert T. & Erwin, Robert D., Jr.
Item Type: Refine your search to only Report
open access

The Effect of the Maxwell Distribution of Velocities on the Neutron Density and Diffusion Length in a Metal Sphere

Description: The change in the simple [formula] distribution of neutrons in a spherical lump of uranium caused by the distribution in velocities of thermal neutrons is calculated. If the calculated curve is fitted as well as possible by a simple [formula] curve, it is shown that the value of [formula] obtained in this way is a function of [formula], the radius of the sphere. For small radii the [formula] obtained in this manner will be as much as 25% greater than the [formula] corresponding to average veloc… more
Date: June 27, 1944
Creator: Plass, Gilbert N.
Item Type: Refine your search to only Report
open access

Electrolytic Reduction of Uranyl Ion

Description: From introduction: "Due to the hydrogen overvoltage at the surface of a mercury cathode, uranium solutions is hydrochloric acid may be reduced not only to the tetravalent state, but until considerable trivalent uranium is formed. Other metallic ions act as oxidation-reduction catalysts as well as being reduced themselves. The following paper is a study of the various reactions taking place in solution and at the surface of the cathode."
Date: May 27, 1946
Creator: Nichols, Ambrose R., Jr.
Item Type: Refine your search to only Report
open access

Experimental Pressure Distributions Over Wing Tips at Mach Number 1.9 1 - Wing Tip With Subsonic Leading Edge

Description: An investigation was conducted at a Mach number of 1.91 to determine spanwise pressure distribution over a wing tip in a region influenced by a sharp subsonic leading edge swept back at 70 degrees. Except for pressure distribution on the top surface in the immediate vicinity of the subsonic leading edge, the maximum difference between linearized theory and experimental data was 2 1/2 percent (of free-stream dynamic pressure) for angles of attack up to 4 degrees and 7 percent for angles of attac… more
Date: January 27, 1949
Creator: Jagger, James M. & Mirels, Harold
Item Type: Refine your search to only Report
open access

Experimentation on the Extraction of Uranium from Western Ores

Description: The following report supplements a previous report by E.R. Saunders and M. C. Carosella and a report by A. J. Gailey and E. O. Brimm based around the same subject. This report describes a number of tests in which leaching temperatures of 115 and 125 C were tried for the extractions of uranium from western ores.
Date: December 27, 1943
Creator: Saunders, E. R. & Carosella, M. C.
Item Type: Refine your search to only Report
open access

An exploratory investigation of the relative merits of split and chord-extension flaps on a 45 degrees swept-back wing

Description: Report presenting a wind-tunnel investigation to explore the merits of split and chord-extension flaps on a 45 degree sweptback wing. Testing occurred at low speed on a semispan model equipped with split flaps of 60 and 90-percent span and a full-span chord-extension flap. Results regarding split flaps, chord-extension flap, and resultant lift coefficients after balancing pitching-moment coefficients are provided.
Date: May 27, 1948
Creator: Hopkins, Edward J.
Item Type: Refine your search to only Report
open access

F-3 and F-4 Engine Tests of Several High-Antiknock Components of Aviation Fuel

Description: Report discussing testing on triptane, hot-acid octane, diisopropyl, neohexane, mixed xylenes, cumene, benzene, toluene, and methyl tert-butyl ether in several blends to determine their knock-limited performance data in F-3 and F-4 engines at standard operating conditions. All of the blending agents examined were found to be usable, with concentrations varying depending on various thermodynamic properties.
Date: November 27, 1944
Creator: Imming, Harry S.; Barnett, Henry C. & Genco, Russell S.
Item Type: Refine your search to only Report
open access

Flight Investigation From High Subsonic to Supersonic Speeds to Determine the Zero-Lift Drag of a Transonic Research Vehicle Having Wings of 45 Degree Sweepback, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Sections

Description: Report presenting rocket-powered flight tests from high subsonic to supersonic speeds and at high Reynolds numbers to determine the zero-lift drag of a transonic wing-body and body-alone configuration. The configuration tested featured a wing of 45 degree sweepback, aspect ratio 4, taper ratio 0.6, and an NACA 65A006 airfoil section, and a body of fineness ratio of 10 and a frontal area equal to 6.06 percent of the wing-plan-form area.
Date: October 27, 1949
Creator: Katz, Ellis
Item Type: Refine your search to only Report
Back to Top of Screen