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115
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34
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23
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19
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359 Matching Results
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The comparative performance of an aviation engine at normal and high inlet air temperatures
"This report presents some results obtained during an investigation to determine the effect of high inlet air temperature on the performance of a Liberty 12 aviation engine. The purpose of this investigation was to ascertain, for normal service carburetor adjustments and a fixed ignition advance, the relation between power and temperature for the range of carburetor air temperatures that may be encountered when supercharging to sea level pressure at altitudes of over 20,000 feet and without intercooling when using plain aviation gasoline and mixtures of benzol and gasoline" (p. 409).
Date:
February 11, 1927
Creator:
Gardiner, Arthur W. & Schey, Oscar W.
System:
The UNT Digital Library
Two-Dimensional Subsonic Compressible Flow Past Elliptic Cylinders
"The method of Poggi is used to calculate, for perfect fluids, the effect of compressibility upon the flow on the surface of an elliptic cylinder at zero angle of attack and with no circulation. The result is expressed in a closed form and represents a rigorous determination of the velocity of the fluid at the surface of the obstacle insofar as the second approximation is concerned. Comparison is made with Hooker's treatment of the same problem according to the method of Janzen and Rayleight and it is found that, for thick elliptic cylinders, the two methods agree very well" (p. 245).
Date:
February 11, 1938
Creator:
Kaplan, Carl
System:
The UNT Digital Library
The Fission Neutron Spectrum of 25
Abstract: "Photographic plates have been used to measure the energy of neutrons from the fission of 25. The spectrum as inferred from the ranges of 850 protons recoiling in the forward direction shows a very wide maximum at ~1.5 Mev with an exponentially decreasing high energy tail which extends beyond 7 Mev. The minimum energy neutrons recorded were ~700 kv. If the spectrum is extrapolated to zero, one finds that this average neutron energy is about 1.85 Mev. The stopping power of the plates was calibrated by the use of monochromatic neutrons from the Li-7(pn) Be-7 reaction and the d-d reaction."
Date:
February 11, 1944
Creator:
Richards, Hugh T. & Perlman, Isadore
System:
The UNT Digital Library
Recalculation of the Critical Size and Multiplication Constant of a Homogeneous UO2 - D2O Mixtures
The multiplication constant and optimal concentration of a slurry pile is recalculated on the basis of Mitchell's recent experiments on resonance absorption. The smallest chain reacting unit contains 45 to 55 m3 of D2O.
Date:
February 11, 1944
Creator:
Wigner, Eugene Paul, 1902-1995; Weinberg, Alvin Martin, 1915-2006 & Stephenson, J.
System:
The UNT Digital Library
300 Area monthly report for January
This report review the work being conducted in the 300 area of the Hanford production facility for the month of January.
Date:
February 11, 1946
Creator:
Kidder, C. P.
System:
The UNT Digital Library
RADON MEASUREMENTS IN WAREHOUSE AND BOX CARS CONTAINING HIGH GRADE ORE
None
Date:
February 11, 1946
Creator:
Anonsen, S.H.
System:
The UNT Digital Library
Computed Temperature Distribution and Cooling of Solid Gas-Turbine Blades
"Computations were made to determine the temperature distribution and cooling of solid gas-turbine blades.A range of temperatures was used from 1500 degrees to 2500 degrees F, blade-root temperatures from 100 degrees to 1000 degrees F, blade thermal conductivity from 8 to 220 BTU/(hr)(sq ft)(degrees F/ft), and net gas to metal heat transfer coefficients from 75 to 250 BTU/(hr)(sq ft)(degrees F)" (p. 1).
Date:
February 11, 1947
Creator:
Reuter, J. George & Gazley, Carl, Jr.
System:
The UNT Digital Library
Cooling of Gas Turbines 1 - Effects of Addition of Fins to Blade Tips and Rotor, Admission of Cooling Air Through Part of Nozzles, and Change in Thermal Conductivity of Turbine Components
"An analysis was developed for calculating the radial temperature distribution in a gas turbine with only the temperatures of the gas and the cooling air and the surface heat-transfer coefficient known. This analysis was applied to determine the temperatures of a complete wheel of a conventional single-stage impulse exhaust-gas turbine. The temperatures were first calculated for the case of the turbine operating at design conditions of speed, gas flow, etc. and with only the customary cooling arising from exposure of the outer blade flange and one face of the rotor to the air" (p. 1).
Date:
February 11, 1947
Creator:
Brown, W. Byron
System:
The UNT Digital Library
Cooling of Gas Turbines, 3, Analysis of Rotor and Blade Temperatures in Liquid-Cooled Gas Turbines
A theoretical analysis of the radial temperature distribution through the rotor and constant cross sectional area blades near the coolant passages of liquid cooled gas turbines was made. The analysis was applied to obtain the rotor and blade temperatures of a specific turbine using a gas flow of 55 pounds per second, a coolant flow of 6.42 pounds per second, and an average coolant temperature of 200 degrees F. The effect of using kerosene, water, and ethylene glycol was determined. The effect of varying blade length and coolant passage lengths with water as the coolant was also determined. The effective gas temperature was varied from 2000 degrees to 5000 degrees F in each investigation.
Date:
February 11, 1947
Creator:
Brown, W. Byron & Livingood, John N. B.
System:
The UNT Digital Library
Development of Inboard Nacelle for the XB-36 Airplane
From Summary: "A series of investigations of several 1/14-scale models of an inboard nacelle for the XB-36 airplane was made in the Langley two-dimensional low-turbulence tunnels. The purpose of these investigations was to develop a low-drag wing-nacelle pusher combination which incorporated an internal air-flow system. As a result of these investigations, a nacelle was developed which had external drag coefficients considerably lower than the original basic form with the external nacelle drag approximately one-half to two-thirds of those of conventional tractor designs. The largest reductions in drag resulted from sealing the gaps between the wing flaps and nacelle, reducing the thickness of the nacelle training-edge lip, and bringing the under-wing air inlet to the wing leading edge."
Date:
February 11, 1947
Creator:
Nuber, Robert J.
System:
The UNT Digital Library
Investigation of Pressure Losses in Several Turbosupercharger Nozzle Hoses
Memorandum presenting surveys of the impact pressure of the flow to obtain information for determining pressure losses in four different turbosupercharger nozzle boxes. The data indicated substantial differences in total head loss among the boxes and the existence of sharply defined high-loss regions in portions of the nozzle annulus.
Date:
February 11, 1947
Creator:
Lord, Albert M. & Donnola, Joseph
System:
The UNT Digital Library
Theoretical Evaluation of Methods of Cooling the Blades of Gas Turbines
A study was made of heat transfer in turbine blades and the effects on blade temperature of cooling the blade root and tip, changing the dimensions of the blades, raising the cycle temperatures, insulating with ceramics, and cooling by circulation of air or water through hollow blades. The results indicated that cooling of the root of the blade, shortening the blade, and cooling hollow blades internally with air or liquid offer possibilities of substantial increases in permissible gas temperatures.
Date:
February 11, 1947
Creator:
Sanders, J. C. & Mendelson, Alexander
System:
The UNT Digital Library
Aerodynamic characteristics of a flying-boat hull having a length-beam ratio of 15 and a warped forebody
From Introduction: "The results of two phases of this investigation, presented in references 1 and 2, have indicated possible ways of reducing hull drag without causing large changes in aerodynamic stability and hydrodynamic performance."
Date:
February 11, 1949
Creator:
MacLeod, Richard G.
System:
The UNT Digital Library
COMPARISON OF VARIOUS METHODS FOR THE REMOVAL OF URANIUM FROM CARBON SALVAGE
None
Date:
February 11, 1949
Creator:
Twichell, L. P.; Petretsky, P. B.; Williams, R. D. & Waldrop, F. B.
System:
The UNT Digital Library
[Office of Hanford Directed Operations events of importance for week ending February 9, 1949]
This report details events of importance reported by the Hanford Operations Office for the week ending February 9, 1949.
Date:
February 11, 1949
Creator:
Travis, J. E.
System:
The UNT Digital Library
Energy Spectrum of Neutrons from 3-10 MEV
The energy distributions of neutrons in the 3-10 Mev energy range resulting from the bombardment of thin U targets are being investigated by the measurement of proton recoils in photographic plates.
Date:
February 11, 1952
Creator:
Adelman, Frank
System:
The UNT Digital Library
Investigation at Mach Number 1.91 of Spreading Characteristics of Jet Expanding From Choked Nozzles
Report presenting an investigation at Mach number 1.91 to determine the gross spreading characteristics of jets expanding from convergent and convergent-divergent nozzles using total-temperature surveys. Results regarding the preliminary development and jet spreading characteristics of the different types of nozzles are provided.
Date:
February 11, 1952
Creator:
Rousso, Morris D. & Baughman, L. Eugene
System:
The UNT Digital Library
Longitudinal Frequency-Response Characteristics of the Douglas D-558-I Airplane as Determined From Experimental Transient-Response Histories to Mach Number of 0.90
Report presenting information regarding transient oscillations observed in response to elevator pulses of the Douglas D-558-I airplane at a range of Mach numbers and altitudes. An application of the Fourier transform was used to obtain the frequency-response characteristics. The effects of lift coefficient on the frequency response are also included.
Date:
February 11, 1952
Creator:
Angle, Ellwyn E. & Holleman, Euclid C.
System:
The UNT Digital Library
Minimum pressure requirements at top of riser -- RDA DC-6, cooling water studies
This report consists of a graph which plots the minimum requirements for the pressure at the top of riser after an electrical power failure verses time after the electrical power failure. Pressure is expressed in pounds per square inch. Points for shutdown of maximum operation and normal operation are given.
Date:
February 11, 1952
Creator:
Nixon, V. D.
System:
The UNT Digital Library
Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail : lateral characteristics
Report presenting an investigation to determine the low-speed lateral characteristics of a triangular-wing airplane model. The model consisted of an aspect ratio 2 triangular wing in combination with a fuselage of fineness ratio 12.5, a thin, triangular, vertical tail with a constant-chord rudder, and a thin, unswept, all-movable horizontal tail.
Date:
February 11, 1952
Creator:
Graham, David & Koenig, David G.
System:
The UNT Digital Library
Time Histories of Maneuvers Performed With an F-86A Airplane During Squadron Operations
Report presenting some preliminary time-history results of maneuvers performed during US Air Force squadron operations with an F-86A jet-fighter airplane. The information covers a speed range from stall to 530 mph-indicated airspeed and pressure altitudes varying from sea level to approximately 25,000 feet.
Date:
February 11, 1952
Creator:
Hamer, Harold A. & Henderson, Campbell
System:
The UNT Digital Library
Flight Measurements of the Stability Characteristics of the Bell X-5 Research Airplane in Sideslips at 59 Degrees Sweepback
"Flight measurements of the stability characteristics of the Bell X-5 research airplane at 59 deg sweepback were made in steady sideslips at Mach numbers from 0.62 to 0.97 at altitudes ranging between 35,000 and 40,000 feet. The results showed that the apparent directional stability was positive and increased at Mach numbers above 0.90. The apparent effective dihedral was positive and high, increasing at Mach numbers above 0.75" (p. 1).
Date:
February 11, 1953
Creator:
Childs, Joan M.
System:
The UNT Digital Library
Preliminary Results of Stability and Control Investigation of the Bell X-5 Research Airplane
"During the acceptance tests of the Bell X-5 airplane, measurements of the static stability and control characteristics and horizontal-tail loads were obtained by the NACA High-Speed Flight Research Station. The results of the stability and control measurements are presented in this paper. A change in sweep angle between 20 deg and 59 deg had a minor effect on the longitudinal trim, with a maximum change of about 2.5 deg in elevator deflection being required at a Mach number near 0.85; however, sweeping the wings produced a total stick-force change of about 40 pounds" (p. 1).
Date:
February 11, 1953
Creator:
Finch, Thomas W. & Briggs, Donald W.
System:
The UNT Digital Library
The T3 (p, y) He4 Reaction
The excitation function for the reaction T3 (p, y) He4 has been extended to proton energies of 7.3 Mev. No experimental evidence is found for a resonance in the reaction up to this energy of bombarding protons.
Date:
February 11, 1953
Creator:
Birge, Robert W. & Jungerman, John A.
System:
The UNT Digital Library