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A method for reducing the temperature of exhaust manifolds

Description: From Summary: "This report describes tests conducted at the Langley Memorial Aeronautical Laboratory on an "air-inducting" exhaust manifold for aircraft engines. The exhaust gases from each cylinder port are discharged into the throat of an exhaust pipe which has a frontal bellmouth. Cooling air is drawn into the pipe, where it surrounds and mixes with the exhaust gases. Temperatures of the manifold shell and of the exhaust gases were obtained in flight for both a conventional manifold and the air-inducting manifold."
Date: September 1931
Creator: Schey, Oscar W. & Young, Alfred W.
Partner: UNT Libraries Government Documents Department

The temperature of unheated bodies in a high-speed gas stream

Description: From Summary: "The present report deals with temperature measurements on cylinders of 0.2 to 3 millimeters diameter in longitudinal and transverse air flow at speeds of 100 to 300 meters per second. Within the explored test range, that is, the probable laminar boundary layer region, the temperature of the cylinders in axial flow is practically independent of the speed and in good agreement with Pohlhausen's theoretical values; Whereas, in transverse flow, cylinders of certain diameter manifest a close relationship with speed, the ratio of the temperature above the air of the body to the adiabatic stagnation temperature decreases with rising speed and then rises again from a Mach number of 0.6. The importance of this "specific temperature" of the body for heat-transfer studies at high speed is discussed."
Date: December 1941
Creator: Eckert, E. & Weise, W.
Partner: UNT Libraries Government Documents Department

Temperatures, thermal stress, and shock in heat-generating plates of constant conductivity and of conductivity that varies linearly with temperature

Description: Report presenting working formulas for the steady-state temperatures and thermal stress in heat-generating infinite plates of constant conductivity. Of all planes in the plate, the plate surfaces are always under the greatest tension, and the midplane is under the greatest compression.
Date: July 1953
Creator: Manson, S. V.
Partner: UNT Libraries Government Documents Department

Temperature recording in high-speed gases

Description: The development of suitable thermometer shapes giving the amount of temperature rise if possible without calibration and affording ready repetition is predicated upon a fundamental elucidation of this heating on a number of elementary body forms. This report provides results of tests at subsonic and supersonic velocities.
Date: August 1941
Creator: Eckert, E.
Partner: UNT Libraries Government Documents Department

Effects of temperature distribution and elastic properties of materials on gas-turbine-disk stresses

Description: Report presenting calculations to determine the influence of changes in temperature distribution and elastic material properties on calculated elastic stresses for a typical gas-turbine disk. Severe temperature gradients caused thermal stresses of sufficient magnitude to reduce the operating safety of the disk.
Date: June 1947
Creator: Holms, Arthur G. & Faldetta, Richard D.
Partner: UNT Libraries Government Documents Department

A biharmonic relaxation method for calculating thermal stress in cooled irregular cylinders

Description: A numerical method was developed for calculating thermal stresses in irregular cylinders cooled by one or more internal passages. The use of relaxation methods and elementary methods of finite differences was found to give approximations to the correct values when compared with previously known solutions for concentric circular cylinders possessing symmetrical and asymmetrical temperature distributions.
Date: May 10, 1951
Creator: Holms, Arthur G.
Partner: UNT Libraries Government Documents Department

Effect of aerodynamic heating on the flutter of a rectangular wing at a Mach number of 2

Description: Report presenting the flutter of a solid wing as affected by aerodynamic heating, which can cause a large momentary loss in torsional stiffness. Both experimental and analytical studies were conducted and good correlation was demonstrated. The loss of stiffness due to aerodynamic heating was calculated and the operational line intersected with the flutter curve.
Date: June 23, 1958
Creator: Runyan, Harry L. & Jones, Nan H.
Partner: UNT Libraries Government Documents Department

Exploratory investigation of boundary-layer transition on a hollow cylinder at a Mach number of 6.9

Description: Report presenting an investigation of the Reynolds number for transition on the outside of a hollow cylinder with heat transfer from the boundary layer to the wall at Mach number 6.9. At a given Mach number, it appears that the Reynolds number based on leading-edge thickness is an important parameter in comparisons of flat-plate transition data from various installations.
Date: February 9, 1956
Creator: Bertram, Mitchel H.
Partner: UNT Libraries Government Documents Department

Exploratory investigation of boundary-layer transition on a hollow cylinder at a Mach number of 6.9

Description: Report presenting an investigation of the Reynolds number for transition on the outside of a hollow cylinder with heat transfer from the boundary layer to the wall at Mach number 6.9. At a given Mach number, it appears that the Reynolds number based on leading-edge thickness is an important parameter in comparisons of flat-plate transition data from various installations.
Date: May 1956
Creator: Bertram, Mitchel H.
Partner: UNT Libraries Government Documents Department

Ignition-delay determinations of furfuryl alcohol and mixed butyl mercaptans with various white fuming nitric acids using modified open-cup and small-scale rocket engine apparatus

Description: Report presenting ignition-delay determinations of furfuryl alcohol and mixed butyl mercaptans with various white fuming nitric acids were made at several temperatures with a modified open-cup apparatus and a small-scale rocket engine of approximately 30-pounds thrust.
Date: February 18, 1955
Creator: Ladanyi, Dezso J.; Miller, Riley O. & Hennings, Glen
Partner: UNT Libraries Government Documents Department

Improvement of high-temperature properties of magnesium-cerium forging alloys

Description: Report presenting an investigation to obtain an improvement in the high-temperature properties and resistance to creep of magnesium-cerium forging alloys. Preliminary testing was carried out to determine the most optimum alloy and then further testing was carried out on different heats of magnesium containing various amounts of cerium.
Date: May 1950
Creator: Grube, K.; Davis, J. A.; Eastwood, L. W.; Lorig, C. H. & Cross, H. C.
Partner: UNT Libraries Government Documents Department

Investigation of 75-millimeter-bore deep-groove ball bearing under radial load at high speeds 2: oil inlet temperature, viscosity, and generalized cooling correlation

Description: Report presenting two 75-millimeter-bore inner-race-riding cage-type ball bearings used in an experimental investigation of the effects of oil inlet temperature and viscosity on bearing operating characteristics over a range of DN values. An increase in oil viscosity produced increased bearing temperatures and caused the power rejected to the oil to be greater with constant DN, load, oil flow, and oil inlet temperature.
Date: September 1953
Creator: Nemeth, Zolton N.; Macks, E. Fred & Anderson, William J.
Partner: UNT Libraries Government Documents Department

Stagnation-point heat transfer to blunt shapes in hypersonic flight, including effects of yaw

Description: An approximate theory is developed for predicting the rate of heat transfer to the stagnation region of blunt bodies in hypersonic flight. Attention is focused on the case where wall temperature is small compared to stagnation temperature. The theoretical heat-transfer rate at the stagnation point of a hemispherical body is found to agree with available experimental data. The effect of yaw on heat transfer to a cylindrical stagnation region is treated at some length, and it is predicted that large yaw should cause sizable reductions in heat-transfer rate.
Date: April 1958
Creator: Eggers, A. J., Jr.; Hansen, C. Frederick & Cunningham, Bernard E.
Partner: UNT Libraries Government Documents Department

Influence of refraction on the applicability of the Zehnder-Mach interferometer to studies of cooled boundary layers

Description: Report presenting an analytical investigation to determine the applicability of the Zehnder-Mach interferometer to two-dimensional cooled-boundary-layer studies. The main factor governing a test section design other than flow characteristics is the estimate of how close to the wall the boundary layer need be studied.
Date: September 1951
Creator: Kinsler, Martin R.
Partner: UNT Libraries Government Documents Department

Investigation of heat transfer from a stationary and rotating ellipsoidal forebody of fineness ratio 3

Description: From Summary: "The convective heat transfer from the surface of an ellipsoidal forebody of fineness ratio 3 and 20-inch maximum diameter was investigated in clear air for both stationary and rotating operation over a range of conditions including air speeds up to 240 knots, rotational speeds up to 1200 rpm, and angles of attack of 0 deg, 3 deg, and 6 deg. The results are presented in the form of heat-transfer coefficients and the correlation of Nusselt and Reynolds numbers. Both a uniform surface temperature and a uniform input heater density distribution were used."
Date: November 1956
Creator: Lewis, James P. & Ruggeri, Robert S.
Partner: UNT Libraries Government Documents Department

Investigation of Heat Transfer from a Stationary and Rotating Conical Forebody

Description: From Summary: "The convective heat transfer from the surface of a conical forebody having a hemispherical nose, an included angle of approximately 30 deg, and. a maximum diameter of 18.9 inches was investigated in a wind tunnel for both stationary and. rotating operation. The range of test conditions included free-stream velocities up to 400 feet per second, rotational speeds up to 1200 rpm, and. angles of attack of 0 deg and 6 deg. Both a uniform surface temperature and a uniform heater input power density were used."
Date: October 1957
Creator: Ruggeri, Robert S. & Lewis, James P.
Partner: UNT Libraries Government Documents Department

Pressure-sensitive system for gas-temperature control

Description: From Summary: "A thermodynamic relation is derived and simplified for use as a temperature-limiting control equation involving measurement of gas temperature before combustion and gas pressures before and after combustion. For critical flow in the turbine nozzles of gas-turbine engines, the control equation is further simplified to require only measurements upstream of the burner. Hypothetical control systems are discussed to illustrate application of the control equations."
Date: March 4, 1948
Creator: Cesaro, Richard S. & Matz, Norman
Partner: UNT Libraries Government Documents Department

A method for determining the rate of heat transfer from a wing or streamline body

Description: From Summary: "A method for calculating the rate of heat transfer from the surface of an airfoil or streamline body is presented. A comparison with the results of an experimental investigation indicates that the accuracy of the method is good. This method may be used to calculate the heat supply necessary for heat de-icing or in ascertaining the heat loss from the fuselage of an aircraft operating at great altitude, for example."
Date: December 1942
Creator: Frick, Charles W., Jr. & McCullough, George B.
Partner: UNT Libraries Government Documents Department

A method for determining the rate of heat transfer from a wing or streamline body

Description: A method for calculating the rate of heat transfer from the surface of an airfoil or streamline body is presented. A comparison with the results of an experimental investigation indicates that the accuracy of the method is good. This method may be used to calculate the heat supply necessary for heat de-icing or in ascertaining the heat loss from the fuselage of an aircraft operating at great altitude. To illustrate the method, the total rate of heat transfer from an airfoil is calculated and compared with the experimental results.
Date: 1945
Creator: Frick, Charles W. & McCullough, George B.
Partner: UNT Libraries Government Documents Department

Cooling of gas turbines 9: cooling effects from use of ceramic coatings on water-cooled turbine blades

Description: From Summary: "The hottest part of a turbine blade is likely to be the trailing portion. When the blades are cooled and when water is used as the coolant, the cooling passages are placed as close as possible to the trailing edge in order to cool this portion. In some cases, however, the trailing portion of the blade is so narrow, for aerodynamic reasons, that water passages cannot be located very near the trailing edge. Because ceramic coatings offer the possibility of protection for the trailing part of such narrow blades, a theoretical study has been made of the cooling effect of a ceramic coating on: (1) the blade-metal temperature when the gas temperature is unchanged, and (2) the gas temperature when the metal temperature is unchanged."
Date: October 13, 1948
Creator: Brown, W. Byron & Livingood, John N. B.
Partner: UNT Libraries Government Documents Department

Structural efficiencies of various aluminum, titanium, and steel alloys at elevated temperatures

Description: Efficient temperature ranges are indicated for two high-strength aluminum alloys, two titanium alloys, and three steels for some short-time compression-loading applications at elevated temperatures. Only the effects of constant temperatures and short exposure to temperature are considered, and creep is assumed not to be a factor. The structural efficiency analysis is based upon preliminary results of short-time elevated-temperature compressive stress-strain tests of the materials. The analysis covers strength under uniaxial compression, elastic stiffness, column buckling, and the buckling of long plates in compression or in shear.
Date: July 1953
Creator: Heimerl, George J. & Hughes, Philip J.
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

Effect of thermal properties on laminar-boundary-layer characteristics

Description: Report presenting an iteration method for solving the laminar-boundary-layer equations for compressible flow in the absence of a pressure gradient when the temperature variation of all the fluid thermal properties is considered. Results in regard to skin friction and heat-transfer characteristics are provided.
Date: March 1953
Creator: Klunker, E. B. & McLean, F. Edward
Partner: UNT Libraries Government Documents Department