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125
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28
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21
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16
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367 Matching Results
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The Measurement of Pressure Through Tubes in Pressure Distribution Tests
"The tests described in this report were made to determine the error caused by using small tubes to connect orifices on the surface of aircraft to central pressure capsules in making pressure distribution tests. Aluminum tubes of 3/16-inch inside diameter were used to determine this error. Lengths from 20 feet to 226 feet and pressures whose maxima varied from 2 inches to 140 inches of water were used. Single-pressure impulses for which the time of rise of pressure from zero to a maximum varied from 0.25 second to 3 seconds were investigated" (p. 303).
Date:
February 23, 1927
Creator:
Hemke, Paul E.
System:
The UNT Digital Library
Wind-Tunnel Tests of a Clark Y Wing With a Narrow Auxiliary Airfoil in Different Positions
"Aerodynamic force tests were made on a combination of a Clark Y wing and a narrow auxiliary airfoil to find the best location of the auxiliary airfoil with respect to the main wing. The auxiliary was a highly cambered airfoil of medium thickness having a chord 14.5 per cent that of the main wing. It was tested in 141 different positions ahead of, above, and behind the nose portion of the main wing, the range of the test points being extended until the best aerodynamic conditions were covered" (p. 537).
Date:
February 23, 1932
Creator:
Weick, Fred E. & Bamber, Millard J.
System:
The UNT Digital Library
Tensile Elastic Properties of Typical Stainless Steels and Nonferrous Metals as Affected by Plastic Deformation and by Heat Treatment
A general discussion is given of the relationships between stress, strain, and permanent set. From stress-set curves are derived proof stresses based on five different percentages of permanent set. The influence of prior plastic extension on these values is illustrated and discussed. A discussion is given of the influence of work-hardening, rest interval, and internal stress on the form of the proof stress-extension curve.
Date:
February 23, 1940
Creator:
McAdam, D. J., Jr. & Mebs, R. W.
System:
The UNT Digital Library
Pile discharge water monitoring. Final report, IDS-19
None
Date:
February 23, 1945
Creator:
Weller, B. L.
System:
The UNT Digital Library
Estimation of Lift and Drag of Airfoils at Near Sonic Speeds and in the Presence of Detached Shock Waves
Report presenting a semiempirical method of estimating the forces on airfoil at near sonic speeds and in the presence of detached shock waves. The calculated values were found to be in good agreement with wind-tunnel testing of the forces on sharp-nose airfoils and two-dimensional wings.
Date:
February 23, 1949
Creator:
Mayer, John P.
System:
The UNT Digital Library
Wind-Tunnel investigation of NACA 65,3-418 airfoil section with boundary-layer control through a single suction slot applied to a plain flap
Report presenting an investigation in the two-dimensional low-turbulence tunnel of the NACA 65,3-418 airfoil section with a 25-percent-airfoil-chord plain flap and a suction slot on the flap. The primary purpose of the investigation is to determine the effect of the type of boundary-layer control on the section lift-drag ratio.
Date:
February 23, 1949
Creator:
Horton, Elmer A. & von Doenhoff, Albert E.
System:
The UNT Digital Library
An 8-Foot Axisymmetrical Fixed Nozzle for Subsonic Mach Numbers Up to 0.99 and for a Supersonic Mach Number of 1.2
From Introduction: "This paper, which should be of interest to those concerned with transonic wind tunnels, covers the design and operating characteristics of the nozzle."
Date:
February 23, 1950
Creator:
Ritchie, Virgil S.; Wright, Ray H. & Tulin, Marshall P.
System:
The UNT Digital Library
Corrosion of Austenitic Stainless Steel Type 347 in Redox Process Stream : (ORNL #1 Flowsheet)
The following report provides the results of laboratory corrosion tests held to investigate the behavior of austenitic stainless steel, Type 347, in selected O.R.N.L. #1 Redox streams.
Date:
February 23, 1950
Creator:
Koenig, W. W.
System:
The UNT Digital Library
Investigation of downwash and wake characteristics at a Mach number of 1.53 3: swept wings
Report presenting the results of an experimental investigation of the downwash and wake characteristics behind two highly swept wings in a supersonic stream. Results regarding the rate of change of downwash with angle of attack at zero lift, variation of downwash angle with angle of attack, and wake are provided.
Date:
February 23, 1950
Creator:
Perkins, Edward W. & Canning, Thomas N.
System:
The UNT Digital Library
Survey of Processes for Radium Recovery from Pitchblende Ores
This general report on radium summarizes the research work conducted by seven AEC contractors since 1943. The costs to concentrate and purify radium from refinery ore residues are discussed. Desriptions and flow sheets of several commercial processes are included to provide background information.
Date:
February 23, 1950
Creator:
Babcock, A. B., Jr.
System:
The UNT Digital Library
Tests of a small-scale NACA submerged inlet at transonic Mach numbers
Report presenting the pressure-recovery characteristics at the vertical center line of an NACA submerged inlet of aspect ratio 5 measured in the Mach number range of 0.60 to 1.08 by the wing-flow method. Variation of ram-recovery ratio determined from measurements at the center line of the inlet with test station Mach number is presented for mass-flow ratios of 0.30 to 0.60. Results regarding the pressure-recovery characteristics and application of the data to fuselage installations are provided.
Date:
February 23, 1950
Creator:
Rolls, L. Stewart & Rathert, George A., Jr.
System:
The UNT Digital Library
Dynamic stability and control characteristics of a vertically rising airplane model in hovering flight
Report presenting an investigation to determine the stability and control characteristics of a vertically rising airplane model. Results of preliminary hovering flight tests are made in still air, away from the interference effects of the ground and side walls, and with normal airplane-type controls operating in the slipstream.
Date:
February 23, 1951
Creator:
Bates, William R.; Lovell, Powell M., Jr. & Smith, Charles C., Jr.
System:
The UNT Digital Library
The effects of Mach number and Reynolds number on the aerodynamic characteristics of several 12-percent-thick wings having 35 degrees of sweepback and various amounts of camber
Report presenting a comparison of the lift, drag, and pitching-moment characteristics of several wings with 35 degrees of sweepback and various amounts of camber in wind-tunnel testing. Six semispan model wings were tested, three with an aspect ratio of 10 and three with an aspect ratio of 5. Results regarding model distortion under aerodynamic loads, effects of Reynolds number, effects of Mach number, and effects of camber are provided.
Date:
February 23, 1951
Creator:
Tinling, Bruce E. & Kolk, W. Richard
System:
The UNT Digital Library
Low-Speed Investigation of a Semisubmerged Air Scoop With and Without Boundary-Layer Suction
"A preliminary low-speed investigation has been made of an air scoop submerged one-half the inlet height in a depression on the surface of a simulated fuselage. Boundary-layer suction was used on the steep approach ramp to improve the internal flow. A 6-degree-included-angle diffuser with an area ratio of 1.9:1 was located behind the inlet in the model. Most of the tests were conducted with an initial turbulent boundary layer believed to approximate that which would occur on the forward part of a fuselage" (p. 1).
Date:
February 23, 1951
Creator:
Pierpont, P. Kenneth & Howell, Robert R.
System:
The UNT Digital Library
Fixation of Mixed Fission Product Activity by Soils of the Savannah River Project
From introduction: "A study of the fission product activity-fixing properties of the Savannah River Project soils was undertaken by this site to provide data for the planning of the waste disposal program for the Savannah River Project."
Date:
February 23, 1952
Creator:
Tesdahl, T. C.; Lowe, C. S.; Mead, F. C. & Murphy, E. L.
System:
The UNT Digital Library
Low-Speed Longitudinal Stability and Lateral-Control Characteristics of a 0.3-Scale Model of the Republic RF-84F Airplane at a Reynolds Number of 9x10(exp 6)
From Summary: "An investigation was conducted in the Langley 19-foot pressure tunnel on a 0.3-scale model of the Republic RF-84F airplane to determine modifications which would eliminate the pitch-up that occurred near maximum lift during flight tests of the airplane. The effects of high-lift and stall-control devices, horizontal tail locations, external stores, and various inlets on the longitudinal characteristics of the model were investigated. For the most part, these tests were conducted at a Reynolds number of 9.0 x 10(exp 6) and a Mach number of 0.19. The results indicated that from the standpoint of stability the inlets should possess blunted side bodies. The horizontal tail located at either the highest or lowest position investigated improved the stability of the model."
Date:
February 23, 1954
Creator:
Bollech, Thomas V. & Kelly, H. Neale
System:
The UNT Digital Library
Aluminum borohydride - hydrocarbon mixtures as a source of ignition for a turbojet combustor
From Introduction: "Data on the extent of decomposition of a sample of aluminum borohy-dride during long-term storage are presented."
Date:
February 23, 1955
Creator:
Foster, Hampton H.; Fletcher, Edward A. & Straight, David M.
System:
The UNT Digital Library
Effect of a Decelerating Grid on Current from an Ion Source
Abstract: "A theoretical criterion is given for the conditions under which the ions from an ion source may be decelerated by a decelerating grid, following the accelerating grid which extracts ions from the emitter, without causing a reduction in the current supplied by the source."
Date:
February 23, 1955
Creator:
Bing, George F., 1924-; Gardner, C. S. & Northrop, Theodore G.
System:
The UNT Digital Library
Effect of fuel nozzle protrusion on transient and steady-state turbojet combustor performance
Report presenting the effect of small variations in the axial position of the liner with respect to the nozzle on limiting rates of change of fuel flow and steady-state combustion efficiencies in a single tubular combustor. Data were obtained with two liner configurations at three combustor-inlet conditions. Results regarding transient combustion performance and steady-state combustion performance are provided.
Date:
February 23, 1955
Creator:
McCafferty, Richard J. & Donlon, Richard H.
System:
The UNT Digital Library
An experimental evaluation of several design variations of hollow turbine blades for expendable engine application
From Summary: "An investigation was made to evaluate several design variations of hollow turbine blades intended for missile-engine use. In one general type, the airfoils were formed from sheet metal; in a second type, the blades were cast. The blades were operated in J47 engine at 7950 rpm turbine speed and 1260 degrees Fahrenheit tail-pipe temperature until a failure occurred or a service life of 30 hours had been attained."
Date:
February 23, 1955
Creator:
Morgan, W. C. & Kemp, R. H.
System:
The UNT Digital Library
Investigation of a Ramp-Type Inlet Designed for Improved Angle-of-Attack Performance at Mach Number 2.0
Report presenting an investigation of an inlet mounted on the side of a fuselage and utilizing a horizontally oriented 14 degree ramp located at the top of the inlet at a variety of Mach numbers. The characteristics of this inlet were compared to a conventional ramp-type side inlet. Results regarding the pressure recovery and model drag coefficients, spillage drag coefficients, and thrust minus drag comparison are provided.
Date:
February 23, 1955
Creator:
Wise, G. A. & Campbell, R. C.
System:
The UNT Digital Library
A Monte Carlo Estimation of the High Energy Neutron Flux Distribution in the ORNL Graphite Reactor
The flux through a given region is proportional to the total lengths of the neutron flight paths that intersect that region. The analytical Monte Carlo procedure manufactured neutron flight paths and totaled the lengths of all paths intercepted by the regions illustrated in Figure 1. The procedure was designed to utilize the various symmetries in the lattice. / Consider a portion of the lattice whose planar cross-section is shown in Figure 5. If R is the region in which the flux is to be estimated and F the fuel rod in which the neutron originated, then flight path P results in an intercepted length whose reflection in the plane is L. On the other hand flight path P' intercepts R' with length L'. R' is not the region to be studied, but a translation of the flight path P' to F' would result in the neutron intercepting R. The origin in P was arbitrary. For each neutron originating in P another could, with equal probability, have originated in P' with parallel paths. Hence consulting L' in R' towards the total flux is equivalent to starting a neutron at P'. Thus consideration of all regions symmetric to R with respect to …
Date:
February 23, 1955
Creator:
Moshman, Jack
System:
The UNT Digital Library
Review of status, methods and potentials of gas-turbine air-cooling
Report presenting an examination of the most promising air-cooled turbine blades for conventional turbojet engines, which are convection-cooled corrugated-insert and strut-supported blades. Successful analytical methods of predicting blade temperatures have been found for both blades. Results regarding turbine-engine performance, turboprop-engine performance, performance variations with compressor-discharge air bleed, and some cooling methods are provided.
Date:
February 23, 1955
Creator:
Esgar, Jack B. & Ziemer, Robert R.
System:
The UNT Digital Library
Some Measurements of Boiling Burn-Out
Report presenting measurements of boiling burn-out heat flux for water flowing upward through an electrically heated tube for ranges of velocity, pressure, length-diameter ratios, and subcooling.
Date:
February 23, 1955
Creator:
Lowdermilk, Warren H. & Weiland, Walter F.
System:
The UNT Digital Library