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The Heat of Formation of Thorium Sesquisulfide

Description: Abstract: "The heat of solution of thorium sesquisulfide was determined in 6.000 molar HCl at 25 C to ascertain the stability of the thorium (III) halides. The molal heat of formation of Th2S3 from rhombic sulfur and crystalline thorium is calculated as 258.6 kcal."
Date: April 7, 1953
Creator: Eyring, LeRoy & Westrum, Edgar F., Jr.
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Heat of Reaction of Chlorine Trifluoride with Water

Description: Abstract: "A measurement of the heat liberated when chlorine trifluoride reacts with water has been made in a simple Dewar calorimeter. The chlorine trifluoride vapor was bubbled into approximately 20 moles of water; the weight of material used, heat equivalent of the calorimeter, and the temperature rise of the water and calorimeter were determined. From these data an average value for the heat of reaction was calculated to be 81.0 +/- 0.4 kcal/mole. Analysis of the reaction solution and evolv… more
Date: October 24, 1950
Creator: Oliver, G. D. & Grisard, J. W.
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The Heat of Solution of Neptunium Metal and the Heats of Formation of some Neptunium Chlorides ; A Microcalorimeter for Heat of Solution Measurements

Description: Due to a need of precise thermodynamical and thermochemical data on these elements and their compounds for the understanding and correlation of the chemical behavior of these substances, this report measures the heat of the solution of neptunium metal and the heats of formation of the neptunium chlorides using a microcalorimeter to measure the heat.
Date: August 1950
Creator: Westrum, Edgar F., Jr. & Eyring, LeRoy
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HEAT RELEASE IN NUCLEAR REACTORS

Description: Discussions are included on energy sources and modes of local deposition of heat, fission fragment and BETA decay energy, neutron energy, energy release by BETA decay of activated nuclei, neutron flux distribution, gamma heating calculations, and integration of the gamma heating equation for simple cases. (M.H.R.)
Date: October 1, 1956
Creator: Alexander, L.G.
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Heat-Requirements for Ice Protection of a Cyclically Gas-Heated, 36 Degree Swept Airfoil with Partial-Span Leading-Edge Slat

Description: From Summary: "Heating requirements for satisfactory cyclic de-icing over a wide range of icing and operating conditions have been determined for a gas-heated, 36 degree swept airfoil of 6.9-foot chord with a partial-span leading-edge slat. Comparisons of heating requirements and effectiveness were made between the slatted and unslatted portions of the airfoil. Studies were also made comparing cyclic de-icing with continuous anti-icing, and cyclic de-icing systems with and without leading-edge … more
Date: May 14, 1956
Creator: Gray, Vernon H. & von Glahn, Uwe H.
open access

HEAT TRANSFER ANALYSIS AND DESIGN OF A PLUGGING INDICATOR SYSTEM FOR SRE

Description: The analysis was performed on a system comprising a counterflow, concentric-pipe economizer, heat exchanger, flowmeter, plug, and connecting pipe. The system was assumed to be at some initial temperature equal to the inlet sodium temperature and suddenly loses heat to a medium in the heat exchanger. Design and operating data are presented. A cooling rate curve is given where the nitrogen flow rate is decreased when the plug temperature reaches 400 deg F. The time variation of minimum temperatur… more
Date: April 1, 1955
Creator: Sletten, H. L.
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Heat Transfer and Boundary-Layer Transition on a Highly Polished Hemisphere-Cone in Free Flight at Mach Numbers Up to 3.14 and Reynolds Numbers Up to 24 X 10(Exp 6)

Description: "A highly polished hemisphere-cone having a ratio of nose radius to base radius of 0.74 and a half-angle of 14.5 degrees was flight tested at Mach numbers up to 4.70. Temperature and pressure data were obtained at Mach numbers up to 3.14 and a free-stream Reynolds number of 24 x 10(exp 6) based on body diameter. The nose of the model had a surface roughness of 2 to 5 microinches as measured with an interferometer" (p. 1).
Date: April 18, 1957
Creator: Buglia, James J.
open access

Heat-transfer and operating characteristics of aluminum forced-convection and stainless-steel natural-convection water-cooled single-stage turbines

Description: Report presenting testing of two water-cooled turbines, one of aluminum alloy using forced-convection cooling and one of stainless steel using natural-convection cooling, to obtain heat-transfer and general operating data like blade temperatures, coolant-flow rates, and coolant pumping losses. Results regarding outside and inside heat-transfer results, coolant pumping power, general operating results, and practical considerations for both are provided.
Date: June 30, 1950
Creator: Freche, John C. & Diaguila, A. J.
open access

Heat Transfer and Pressure Distribution at a Mach Number of 6.8 on Bodies With Conical Flares and Extensive Flow Separation

Description: Report presenting an investigation of heat transfer and pressure distribution on flared bodies under laminar, transitional, and turbulent boundary-layer conditions at Mach number 6.8. Information about flow characteristics, flare drag, and the relationship between flare drag and flare heating is provided.
Date: July 20, 1956
Creator: Becker, John V. & Korycinski, Peter F.
open access

Heat-Transfer and Pressure Distribution on Six Blunt Noses at a Mach Number of 2

Description: Report presenting testing on six blunt-nose models at angles of attack ranging from 0 to 5 degrees in order to evaluate the heat transfer and pressure on their surfaces. Information about transition, proper design, and locations of greatest and least heat transfer is provided.
Date: April 18, 1957
Creator: Carter, Howard S. & Bressette, Walter E.
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Heat Transfer and Pressure Loss in Tube Bundles for High Performance Heat Exchangers and Fuel Elements

Description: From introduction: "The tube arrangement covered in this report was proposed in June, 1950, as a means of halving the weight and volume required for the heat exchanger. Ideally, the pressure drop across this arrangement should be little more than that required to overcome the skin friction on the tube surfaces. If the pressure drop across the tube spacers and in the cross-flow regions can be kept low, this ideal can be approached. much of the test work covered in this report was devoted to this… more
Date: August 12, 1952
Creator: Cohen, G. H.; Fraas, A. P. & LaVerne, M. E.
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Heat-Transfer and Pressure Measurements from a Flight Test of a 1/18-Scale Model of the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.95 and Reynolds Number Per Foot of 23 by 10 to the 6th Power

Description: Report discussing the boundary-layer transition and heat-transfer measurements for a model of the Titan intercontinental ballistic missile up to a specified Mach and Reynolds number. Boundary-layer transition was observed on the nose of the missile. The drag coefficient for a variety of Mach numbers was also obtained.
Date: December 19, 1957
Creator: Graham, John B., Jr.; Chauvin, Leo T. & Speegle, Katherine C.
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Heat-Transfer and Pressure Measurements From a Flight Test of a 1/18-Scale Model of the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.95 and Reynolds Number Per Foot of 23 X 10(Exp 6): Coord. No. AF-AM-70

Description: "Boundary-layer transition and heat-transfer measurements were obtained from a flight test of a 1/18-scale model of the Titan intercontinental ballistic missile up to a Mach number of 3.95 and a Reynolds number per foot of 23 x 10(exp 6). Boundary-layer transition was observed on the nose of the model. Available theories predicted heat-transfer coefficients reasonably well for the fully laminar or turbulent flow conditions. The drag coefficient of the configuration was also obtained for a Mach … more
Date: December 19, 1957
Creator: Graham, John B., Jr.; Chauvin, Leo T. & Speegle, Katherine C.
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Heat-Transfer and Pressure Measurements From a Flight Test of the Second 1/18-Scale Model of the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.91 and Reynolds Number Per Foot of 23.4 by 10 to the 6th Power

Description: Report discussing heat-transfer and pressure measurements obtained from flight testing of a model of the Titan intercontinental ballistic missile up to a specified Mach and Reynolds number. The heat-transfer coefficients were compared to theoretical results and a discrepancy was found during the accelerating portions of flight. Drag coefficients were obtained for a range of Mach numbers.
Date: January 29, 1958
Creator: Graham, John B., Jr.
open access

Heat-Transfer and Pressure Measurements From a Flight Test of the Second 1/18-Scale Model on the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.91 and Reynolds Number Per Foot of 23.4 X 10(Exp 6) : Coord. No. AF-AM-70

Description: Report presenting heat-transfer and pressure measurements obtained from flight tests of a model of the Titan intercontinental ballistic missile. Turbulent flow was observed over the model throughout the flight with the exception of one station on the nose. Results regarding pressure measurements, heat transfer, and drag measurements are required.
Date: January 29, 1958
Creator: Graham, John B., Jr.
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Heat-transfer and pressure measurements on flat-faced cylinders at a Mach number of 2

Description: Report presenting flat-faced cylinders tested at Mach number 2 and sea-level conditions in the preflight jet. Both pressure distributions and heat-transfer rates were measured. Results regarding pressure measurements and heat-transfer measurements are provided.
Date: July 1958
Creator: Stoney, William E., Jr. & Markley, J. Thomas
open access

Heat transfer and recovery temperatures on a sphere with laminar, transitional, and turbulent boundary layers at Mach numbers of 2.00 and 4.15

Description: Report presenting an investigation of the pressure and equilibrium-temperature distributions on a sphere at Mach numbers of 2.00 and 4.15. The local aerodynamic heat transfer was measured on a sphere at Mach number 2.00 and on a hemisphere-cylinder at Mach number 4.15. Results regarding pressure distributions, equilibrium and recovery temperatures, heat-transfer coefficients, and effect of roughness on transition are provided.
Date: December 1957
Creator: Beckwith, Ivan E. & Gallagher, James J.
open access

Heat Transfer and Skin Friction by an Integral Method in the Compressible Laminar Boundary Layer With a Streamwise Pressure Gradient

Description: Note presenting a simplified method developed for the calculation of heat transfer and skin friction in the compressible boundary layer with an arbitrary Prandtl number near unity and an arbitrary streamwise pressure gradient and wall temperature distribution. The method maybe extended to calculation of heat transfer with equilibrium dissociation provided the wall temperature is below dissociation temperatures.
Date: September 1953
Creator: Beckwith, Ivan E.
open access

Heat Transfer and Thermal Stresses in Nuclear Reactor Shells

Description: A method is presented for determining heat transfer rates and thermal stresses from the gamma-ray energy absorption of nuclear reactor shells for plane, cylindrical, and spherical geometries. Criteria for minimizing thermal stresses are developed, along with the corresponding external cooling rates necessary to minimize the thermal stress. Design charts are presented for rapid determination of approximate thermal stresses and heat transfer rates, along with a numerical example illustrating the … more
Date: September 1953
Creator: Durham, Franklin P.
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Heat Transfer and Thermal Stresses in Sandwich Panels

Description: Note presenting calculated maximum temperature differences between faces and calculated thermal stresses for sandwich panels with a prescribed linear rate of temperature rise and at one face and with the other face insulated. Maximum temperature differences between top and bottom faces are considerably less when both radiation and conduction are considered than when radiation is neglected. Results regarding dimensionless analysis, correlation of theory and experiment, and thermal stresses are p… more
Date: September 1958
Creator: Swann, Robert T.
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Heat transfer at the forward stagnation point of blunt bodies

Description: Report presenting relations for the calculation of heat transfer at the forward stagnation point of both two-dimensional and axially symmetric blunt bodies. The relations for the heat transfer, which were obtained from exact solutions to the equations of the laminar boundary layer, are presented in terms of local velocity gradient at the stagnation point.
Date: July 1955
Creator: Reshotko, Eli & Cohen, Clarence B.
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Heat transfer burnout of Mark VIII fuel

Description: The operating conditions to which the special Mark VIII quatrefoils will be exposed during the proposed piloting program have been compared with the conditions required to cause burnout, using an established method of calculating these conditions. The results of this comparison permit the following conclusions to be drawn: (1) With normal flow of coolant through the special elements the heat flux to be encountered in the R-8 cycle (1400 MW) will be 70% or that required to cause burnout (30% mar… more
Date: August 1, 1956
Creator: Bernath, L.
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