12 Matching Results

Search Results

Advanced search parameters have been applied.

Pressure losses of titanium and magnesium slurries in pipes and pipeline transitions

Description: Report presenting comparisons of experimental and calculated pressure losses for Newtonian non-Newtonian materials. The transition loss coefficients obtained for the Newtonian and non-Newtonian materials and those reported in the literature for Newtonian fluids agree within the errors of experiment.
Date: January 1957
Creator: Weltmann, Ruth N. & Keller, Thomas A.
Partner: UNT Libraries Government Documents Department

An evaluation of non-Newtonian flow in pipe lines

Description: Report presenting an analysis of a method for determining pressure losses due to the flow of non-Newtonian materials in pipe lines by using basic flow data obtained from measurements of flow curves, which are rate-of-shear-shear-stress curves. Reported flow and pressure data are analyzed. The validity of the generalized friction diagram for describing flow of Bingham plastics in pipe lines is shown by an evaluation of experimental data of two independent investigators.
Date: February 1955
Creator: Weltmann, Ruth N.
Partner: UNT Libraries Government Documents Department

Prediction of losses induced by angle of attack in cascades of sharp-nosed blades for incompressible and subsonic compressible flow

Description: Report presenting a method of computing the losses in total pressure caused by a non-zero angle of attack at the inlet to a row of sharp-nosed blades for both incompressible and subsonic compressible flow. The method is based on momentum considerations across a row of zero-thickness flat plates and assumes that the blade force is normal to the plate surface.
Date: January 1955
Creator: Kramer, James J. & Stanitz, John D.
Partner: UNT Libraries Government Documents Department

Variation with Mach Number of Static and Total Pressures Through Various Screens

Description: "Tests were conducted in the Langley 24-inch highspeed tunnel to ascertain the static-pressure and total-pressure losses through screens ranging in mesh from 3 to 12 wires per inch and in wire diameter from 0.023 to 0.041 inch. Data were obtained from a Mach number of approximately 0.20 up to the maximum (choking) Mach number obtainable for each screen. The results of this investigation indicate that the pressure losses increase with increasing Mach number until the choking Mach number, which can be computed, is reached" (p. 1).
Date: February 1946
Creator: Adler, Alfred A.
Partner: UNT Libraries Government Documents Department

A Method for Estimating the Effect of Turbulent Velocity Fluctuations in the Boundary Layer on Diffuser Total-Pressure-Loss Measurements

Description: Note presenting a method for estimating the effect of turbulent velocity fluctuations on diffuser total-pressure-loss measurements. When the longitudinal velocity fluctuations are large, as evidenced by discrepancies between the inlet and exit weight flows, the method compensates for the discrepancies by adjusting the boundary-layer profile.
Date: January 1954
Creator: Persh, Jerome & Bailey, Bruce M.
Partner: UNT Libraries Government Documents Department

Theoretical Loss Relations for Low-Speed Two-Dimensional-Cascade Flow

Description: Note presenting a theoretical analysis of the relations between wake characteristics and total-pressure defect for the incompressible flow across a two-dimensional cascade of compressor blades. Results indicated that the total-pressure-loss coefficient for unseparated flow varied almost directly with the ratio of wake momentum thickness to blade chord length and with the solidity, and inversely with the cosine of the air outlet angle.
Date: March 1956
Creator: Lieblein, Seymour & Roudebush, William H.
Partner: UNT Libraries Government Documents Department

Icing Characteristics and Anti-Icing Heat Requirements for Hollow and Ternally Modified Gas-Heated Inlet Guide Vanes

Description: "A two-dimensional inlet-guide-vane cascade was investigated to determine the effects of ice formations on the pressure losses across the guide vanes and to evaluate the heated gas flow and temperature required to prevent Icing at various conditions. A gas flow of approximately 0.4 percent of the inlet-air flow was necessary for anti-icing a hollow guide-vane stage at an inlet-gas temperature of 500 F under the following icing conditions: air velocity, 280 miles per hour; water content, 0.9 gram per cubic meter; and Inlet-air static temperature, 00 F. Also presented are the anti-icing gas flows required with modifications of the hollow Internal gas passage, which show heat input savings greater than 50 percent" (p. 1).
Date: December 5, 1950
Creator: Gray, Vernon H. & Bowden, Dean T.
Partner: UNT Libraries Government Documents Department

Comparison of pressure-loss characteristics of several tail-cone air-induction systems for air-cooled gas-turbine rotors

Description: Report presenting testing of three scale models and a full-scale configuration of systems for ducting cooling air through a turbojet engine tail cone to a cooled turbine rotor in order to determine pressure-loss characteristics.
Date: January 12, 1953
Creator: Smith, Gordon T. & Curren, Arthur N.
Partner: UNT Libraries Government Documents Department

Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine 6 - Analysis of Effects of Inlet Pressure Losses

Description: The losses in the inlet air ducts, the diffusers, and the de-icing equipment associated with turbojet engine installations cause a reduction in the total pressure at the inlet of the engine and result in reduced thrust and increased specific fuel consumption. An analytical evaluation of the effects of inlet losses on the net thrust and the fuel economy of a 3000-pound-thrust axial flow turbojet engine with a two-stage turbine is presented. The analysis is based on engine performance characteristics that were determined from experiments in the NACA Cleveland altitude wind tunnel.
Date: 1948
Creator: Sanders, Newell D. & Palasics, John
Partner: UNT Libraries Government Documents Department

Investigation of the pressure-loss characteristics of a turbojet inlet screen

Description: Report presenting the results of an investigation to determine the static-pressure losses and total-pressure distributions of a turbojet inlet screen. The screen was tested in two configurations: one with the vane leading edges square and rough and the other with the vane leading edges rounded. Results regarding the static-pressure-loss coefficient, corrected static-pressure loss, and total-pressure distributions are provided.
Date: September 1947
Creator: Lankford, John L.
Partner: UNT Libraries Government Documents Department

Comparison of several methods of predicting the pressure loss at altitude across a baffled aircraft-engine cylinder

Description: Report presenting several methods of predicting the compressible-flow pressure loss across a baffled aircraft-engine cylinder that were analytically and experimentally investigated on a typical air-cooled aircraft-engine cylinder. Results regarding the evaluation of data, comparative accuracy of correction methods, and ability to apply information about heat transfer to compressible-flow pressure-drop predictions are provided.
Date: May 1946
Creator: Neustein, Joseph & Schafer, Louis J., Jr.
Partner: UNT Libraries Government Documents Department