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Investigation of equilibrium temperatures and average laminar heat-transfer coefficients for the front half of swept circular cylinders at a Mach number of 6.9

Description: Report presenting the average heat-transfer coefficients and equilibrium temperatures for the front half of an isothermal cylinder with a laminar boundary layer as determined by wind tunnel testing at Mach number 6.9 and a range of Reynolds numbers and sweep angles.
Date: August 18, 1955
Creator: Feller, William V.
Partner: UNT Libraries Government Documents Department

Measurements of heat-transfer and friction coefficients for air flowing in a tube of length-diameter ratio of 15 at high surface temperatures

Description: Report presenting measurements of average heat-transfer and friction coefficients for air flowing through a smooth, electrically heated tube with a bellmouth entrance with a length-to-diameter ratio of 15 and a range of average surface temperatures, Reynolds numbers, exit Mach numbers, and heat fluxes. Results regarding the axial-wall-temperature distribution, heat balance, correlation of heat-transfer coefficients, and correlation of friction coefficient are provided.
Date: July 9, 1953
Creator: Weiland, Walter F. & Lowdermilk, Warren H.
Partner: UNT Libraries Government Documents Department

Heat transfer to bodies in a high-speed rarefied-gas stream

Description: Report presenting measurements of the equilibrium temperature and heat-transfer coefficients for transverse cylinders in a high-speed stream of rarefied gas over a range of Knudsen and Mach numbers. Results regarding the temperature recovery for an insulated body and heat-transfer-test results are provided.
Date: August 1951
Creator: Stalder, Jackson R.; Goodwin, Glen & Creager, Marcus O.
Partner: UNT Libraries Government Documents Department

Heat transfer to bodies in a high-speed rarified-gas stream

Description: Report presents the results of an investigation to determine the equilibrium temperature and heat-transfer coefficients for transverse cylinders in a high-speed stream of rarefied gas measured over a range of Knudsen numbers (ratio of molecular-mean-free path to cylinder diameter) from 0.025 to 11.8 and for Mach numbers from 2.0 to 3.3. The range of free-stream Reynolds numbers was from 0.28 to 203. The models tested were 0.0010-, 0.0050-, 0.030-, 0.051-, 0.080-, and 0.126-inch -diameter cylinders held normal to the stream.
Date: May 14, 1951
Creator: Stalder, Jackson R.; Goodwin, Glen & Creager, Marcus O.
Partner: UNT Libraries Government Documents Department

Extension of boundary-layer heat-transfer theory to cooled turbine blades

Description: An equation for average heat transfer of a surface was derived when the boundary layer changed from laminar to turbulent. Influences on the heat transfer through a laminar boundary layer of Mach number, temperature ratio (gas temperature divided by wall temperature), and exponents of gas-property temperature relations were shown to be relatively small for air with Mach numbers less than 2 and temperature ratios between 1 and 4. Good agreement was obtained with experimental results from cylinders, an airfoil, and turbine blades.
Date: August 11, 1950
Creator: Brown, W. Byron & Donoughe, Patrick L.
Partner: UNT Libraries Government Documents Department

Turbulent convective heat-transfer coefficients measured from flight tests of four research models (NACA RM-10) at Mach numbers from 1.0 to 3.6

Description: Report presenting an evaluation of convective heat-transfer coefficients from skin temperatures measured along the body of a research model designated NACA RM-10. Heat-transfer data is presented for a range of Mach and Reynolds numbers based on the axial distance from the nose to the point at which the temperature measurements were made. Results regarding the recovery factor, heat transfer, correlation with different aircraft models, and Reynolds analogy are provided.
Date: March 11, 1955
Creator: Chauvin, Leo T. & Maloney, Joseph P.
Partner: UNT Libraries Government Documents Department

Preliminary investigation of the transfer of heat from a flat plate at a Mach number of 1.5

Description: From Summary: "Surface temperatures and heat transfer to the air stream have been measured for turbulent flow over a flat plate at a Mach number of 1.5 and at a Reynolds number, based on the momentum thickness of the boundary layer, of approximately 5000. Preliminary data are presented and the surface heat-transfer coefficients calculated from these data are considered to be accurate to plus or minus 2.6 percent at a temperature potential of 50 degrees Fahrenheit. These data are in good agreement with the results produced by applying modifications obtained from published information to existing subsonic theories."
Date: December 13, 1951
Creator: Emmons, M. A., Jr. & Blanchard, R. F.
Partner: UNT Libraries Government Documents Department

Laminar friction and heat transfer at Mach numbers from 1 to 10

Description: Velocity and temperature profiles and laminar boundary-layer characteristics have been computed for Mach numbers from 1 to 10, utilizing experimental values of the heat capacity, viscosity, and conductivity. The analysis shows that effective temperature, which is a function of the surface temperature and stream conditions, arises naturally and is the proper reference temperature to be used in heat-transfer calculations. The effective temperature and the recovery temperature become identical for the condition of zero heat transfer.
Date: October 1951
Creator: Klunker, E. B. & McLean, F. Edward
Partner: UNT Libraries Government Documents Department

Determination of average heat-transfer coefficients for a cascade of symmetrical impulse turbine blades 1: heat transfer from blades to cold air

Description: Report presenting an investigation to determine average outside surface heat-transfer coefficients for a cascade of symmetrical impulse turbine blades. Results regarding recovery factor, heat-transfer coefficients, effective gas temperature, turbine cascades, cylinders and streamline bodies, and application to rim-cooling theory are provided.
Date: November 10, 1948
Creator: Meyer, Gene L.
Partner: UNT Libraries Government Documents Department

Slip-flow heat transfer from cylinders in subsonic airstreams

Description: Report presenting over 1000 measured convective heat-transfer coefficients for normal cylinders in subsonic slip flow that have been correlated by using Nusselt number as a function of Reynolds and Knudsen (or Mach) numbers. A complicated nonlinear dependence of the heat-transfer coefficient to the difference between cylinder and recovery temperature is reported. The application of these results to hot-wire anemometry is also discussed.
Date: September 1958
Creator: Baldwin, Lionel V.
Partner: UNT Libraries Government Documents Department

Surface heat-transfer coefficients of finned cylinders

Description: An investigation to determine and correlate the experimental surface heat-transfer coefficients of finned cylinders with different air-stream cooling arrangements was conducted at the Langley Memorial Aeronautical Laboratory from 1932 to 1938. The investigation covered the determination of the effect of fin width, fin space, fin thickness, and cylinder diameter on the heat transfer. Wind-tunnel tests were made in the free air stream with and without baffles and also with various devices for creating a turbulent air stream. Tests were also made with blower.
Date: April 27, 1939
Creator: Ellerbrock, Herman H., Jr. & Biermann, Arnold E.
Partner: UNT Libraries Government Documents Department

Measurement of heat-transfer and friction coefficients for flow of air in noncircular ducts at high surface temperatures

Description: Report presenting measurements of average heat-transfer and friction coefficients obtained with air flowing through electrically heated ducts with square, rectangular, and triangular cross sections for a range of surface temperatures and Reynolds numbers. Results regarding heat balances, correlation of heat-transfer coefficients, correlation of friction coefficients, and correlation of peripheral temperature variations are provided.
Date: January 25, 1954
Creator: Lowdermilk, Warren H.; Weiland, Walter F., Jr. & Livingood, John N. B.
Partner: UNT Libraries Government Documents Department

Heat-transfer measurements on two bodies of revolution at a Mach number of 3.12

Description: Report presenting local rates of heat transfer obtained from a parabolic-nosed cylinder at Mach number 3.12. The laminar-heat-transfer coefficients obtained from the conical portion of the cone cylinder were found to agree closely with theory at all temperature levels when corrected for the axial temperature distribution.
Date: October 1956
Creator: Jack, John R. & Diaconis, N. S.
Partner: UNT Libraries Government Documents Department

Preliminary heat-transfer studies on two bodies of revolution at angle of attack at a Mach number of 3.12

Description: Report presenting local rates of heat transfer obtained for a cone-cylinder model and a parabolic-nosed-cylinder model at Mach number 3.12 and a range of angles of attack. For similar type boundary layers, heat-transfer coefficients at angle of attack were always higher than those at zero angle of attack at corresponding geometric locations.
Date: September 1958
Creator: Sands, Norman & Jack, John R.
Partner: UNT Libraries Government Documents Department

Turbulent-heat-transfer measurements at a Mach number of 1.62

Description: Report presenting turbulent-heat-transfer measurements obtained through the use of an axially symmetric annular nozzle consisting of an inner, shaped center body and an outer cylindrical sleeve for a Mach number of 1.62. Results regarding wall temperatures, variation of local Nusselt number with local Reynolds number, density, viscosity, and variation of local temperature-recovery factor with local Reynolds number are provided.
Date: June 1955
Creator: Brevoort, Maurice J. & Rashis, Bernard
Partner: UNT Libraries Government Documents Department

Turbulent-heat-transfer measurements at a Mach number of 3.90

Description: Report presenting turbulent-heat-transfer measurements obtained through the use of an axially symmetric annual nozzle consisting of an inner shaped center body and an outer cylindrical sleeve at Mach number 3.90. Results regarding the variation of wall temperature with longitudinal distance, variation of local Nusselt number with local Reynolds number, and variation of local temperature-recovery factor with local Reynolds number are provided.
Date: July 1956
Creator: Brevoort, Maurice J.
Partner: UNT Libraries Government Documents Department

Turbulent-heat-transfer measurements at a Mach number of 3.03

Description: Report presenting turbulent-heat-transfer measurements obtained through the use of a three-dimensional axially symmetric annual nozzle consisting of an inner shaped plug and an outer cylindrical sleeve at Mach number 3.03. Results regarding the variation of wall temperature with longitudinal distance, variation of local Nusselt number with local Reynolds number, and variation of local temperature-recovery factor with local Reynolds number are provided.
Date: September 1954
Creator: Brevoort, Maurice J. & Rashis, Bernard
Partner: UNT Libraries Government Documents Department

Calculations of Laminar Heat Transfer Around Cylinders of Arbitrary Cross Section and Transpiration-Cooled Walls with Application to Turbine Blade Cooling

Description: An approximate method for development of flow and thermal boundary layers in laminar regime on cylinders with arbitrary cross section and transpiration-cooled walls is obtained by use of Karman's integrated momentum equation and an analogous heat-flow equation. Incompressible flow with constant property values throughout boundary layer is assumed. Shape parameters for approximated velocity and temperature profiles and functions necessary for solution of boundary-layer equations are presented as charts, reducing calculations to a minimum. The method is applied to determine local heat-transfer coefficients and surface temperature-cooled turbine blades for a given flow rate. Coolant flow distributions necessary for maintaining uniform blade temperatures are also determined.
Date: September 24, 1951
Creator: Eckert, E. R. G. & Livingood, John N. B.
Partner: UNT Libraries Government Documents Department

Measurements of Recovery Factors and Coefficients of Heat Transfer in a Tube for Subsonic Flow of Air

Description: Note presenting measurements of heat flow to air at subsonic velocities and substantially constant Reynolds number, which show that the heat-transfer coefficient is independent of the difference between the temperature of the heated wall and the adiabatic wall temperature. Recovery factors are measured at the pipe wall for adiabatic flow.
Date: June 1945
Creator: McAdams, William H.; Nicolai, Lloyd A. & Keenan, Joseph H.
Partner: UNT Libraries Government Documents Department

Heat-Transfer Tests of a Steel Cylinder Barrel With Aluminum Fins

Description: Report presenting tests conducted on a steel cylinder barrel with aluminum fins in order to determine the heat-transfer coefficients of the cylinder and the excellence of the bond between the steel barrel and the aluminum fins. Results regarding the heat-transfer tests and physical tests are provided.
Date: August 1939
Creator: Ellerbrock, Herman H., Jr.
Partner: UNT Libraries Government Documents Department

Preliminary Results of Heat Transfer from a Stationary and Rotating Ellipsoidal Spinner

Description: Convective heat-transfer coefficients in dry air were obtained for an ellipsoidal spinner of 30-inch maximum diameter for both stationary and rotating operation over a range of conditions including airspeeds up to 275 miles per hour, rotational speeds up to 1200 rpm, and angles of attack of zero and 40 The results are presented in terms of Nusselt numbers, Reynolds numbers, and convective heat-transfer coefficients. The studies included both uniform heating densities over the spinner and uniform surface temperatures.. In general, the results showed that rotation will increase the convective heat transfer from a spinner, especially in the turbulent-flow regions. Rotation of the spinner at 1200 rpm and at a free-stream velocity of 275 miles per hour increased the Nusselt number parameter in the turbulent-flow region by 32 percent over that obtained with a stationary spinner; whereas in the nose region, where the flow was laminar, an increase of only 18 percent was observed. Transition from laminar to turbulent flow occurred over a large range of Reynolds numbers primarily because of surface roughness of the spinner. Operation at an angle of attack of 40 had only small effects on the local convective heat transfer for the model studied.
Date: August 6, 1953
Creator: von Glahn, U.
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

Turbulent and laminar heat-transfer measurements on a 1/6-scale NACA RM-10 missile in free fight to Mach number of 4.2 and to a wall temperature of 1400 degrees R

Description: Report presenting aerodynamic-heating data obtained from Mach numbers 1.2 to 4.2 from a free-flight test of a model finless NACA RM-10. Skin temperatures were measured at six stations along the body. Results regarding experimental recovery factors and Stanton number are provided.
Date: July 3, 1956
Creator: Piland, Robert O.; Collie, Katherine A. & Stoney, William E.
Partner: UNT Libraries Government Documents Department