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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Research Memorandums
 Collection: National Advisory Committee for Aeronautics Collection
Effect of ice formations on section drag of swept NACA 63A-009 airfoil with partical-span leading-edge slat for various modes of thermal ice protection

Effect of ice formations on section drag of swept NACA 63A-009 airfoil with partical-span leading-edge slat for various modes of thermal ice protection

Date: March 15, 1954
Creator: Von Glahn, Uwe H & Gray, Vernon H
Description: Studies were made to determine the effect of ice formations on the section drag of a 6.9-foot-chord 36 degree swept NACA 63A-009 airfoil with partial-span leading-edge slat. In general, the icing of a thin swept airfoil will result in greater aerodynamic penalties than for a thick unswept airfoil. Glaze-ice formations at the leading edge of the airfoil caused large increases in section drag even at liquid-water content of 0.39 gram per cubic meter. The use of an ice-free parting strip in the stagnation region caused a negligible change in drag compared with a completely unheated airfoil. Cyclic de-icing when properly applied caused the drag to decrease almost to the bare-airfoil drag value.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of turbines for driving supersonic compressors II : performance of first configuration with 2.2 percent reduction in nozzle flow area / Warner L. Stewart, Harold J. Schum, Robert Y. Wong

Investigation of turbines for driving supersonic compressors II : performance of first configuration with 2.2 percent reduction in nozzle flow area / Warner L. Stewart, Harold J. Schum, Robert Y. Wong

Date: July 22, 1952
Creator: Stewart, Warner L; Schum, Harold J & Wong, Robert Y
Description: The experimental performance of a modified turbine for driving a supersonic compressor is presented and compared with the performance of the original configuration to illustrate the effect of small changes in the ratio of nozzle-throat area to rotor-throat area. Performance is based on the performance of turbines designed to operate with both blade rows close to choking. On the basis of the results of this investigation, the ratio of areas is concluded to become especially critical in the design of turbines such as those designed to drive high-speed, high-specific weight-flow compressors where the turbine nozzles and rotor are both very close to choking.
Contributing Partner: UNT Libraries Government Documents Department
Tabulated pressure coefficients and aerodynamic characteristics measured in flight on the wing of the D-558-I research airplane through a Mach number range of 0.80 to 0.89 and throughout the normal-force-coefficient range at Mach numbers of 0.61, 0.7

Tabulated pressure coefficients and aerodynamic characteristics measured in flight on the wing of the D-558-I research airplane through a Mach number range of 0.80 to 0.89 and throughout the normal-force-coefficient range at Mach numbers of 0.61, 0.7

Date: August 20, 1951
Creator: Keener, Earl R; Bandish, Rozalia M & NACA
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Altitude-chamber performance of British Rolls-Royce Nene II engine III : 18.00-inch-diameter jet nozzle

Altitude-chamber performance of British Rolls-Royce Nene II engine III : 18.00-inch-diameter jet nozzle

Date: July 10, 1950
Creator: Grey, Ralph E; Brightwell, Virginia L; Barson, Zelmar & NACA
Description: An altitude-chamber investigation of British Rolls-Royce Nene II turbojet engine was conducted over range of altitudes from sea level to 65,000 feet and ram pressure ratios from 1.10 to 3.50, using an 18.00-inch-diameter jet nozzle. The 18.00-inch-diameter jet nozzle gave slightly lower values of net-thrust specific fuel consumption than either the 18.41- or the standard 18.75-inch-diameter jet nozzles at high flight speeds. At low flight speeds, the 18.41-inch-diameter jet nozzle gave the lowest value of net-thrust specific fuel consumption.
Contributing Partner: UNT Libraries Government Documents Department
Development of a supersonic area rule and an application to the design of a wing-body combination having high lift-to-drag ratios

Development of a supersonic area rule and an application to the design of a wing-body combination having high lift-to-drag ratios

Date: January 1, 1953
Creator: Fischetti, T. L. & Whitcomb, R. T.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wing pressure distributions over the lift range of the convair xf-92a delta-wing airplane at subsonic and transonic speeds

Wing pressure distributions over the lift range of the convair xf-92a delta-wing airplane at subsonic and transonic speeds

Date: November 30, 1955
Creator: Jordan, G. H. & Keener, E. R.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of rate, area, and distribution of impingement of waterdrops on various airfoils from trajectories obtained on the differential analyzer

Determination of rate, area, and distribution of impingement of waterdrops on various airfoils from trajectories obtained on the differential analyzer

Date: February 16, 1949
Creator: Guibert, A. G.; Janssen, E. & Robbins, W. M.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Compilation and Analysis of US Turbojet and Ram-Jet Engine Characteristics

Compilation and Analysis of US Turbojet and Ram-Jet Engine Characteristics

Date: November 27, 1956
Creator: Cesaro, R. S. & Walker, C. L.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Material compatibility with gaseous fluorine

Material compatibility with gaseous fluorine

Date: January 1, 1957
Creator: Douglass, H. W. & Price, H. G., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An Anaylsis of Control Requirements and Control Parameters for Direct-Coupled Turbojet Engines

An Anaylsis of Control Requirements and Control Parameters for Direct-Coupled Turbojet Engines

Date: January 1, 1947
Creator: Novik, David & Otto, Edward W.
Description: Requirements of an automatic engine control, as affected by engine characteristics, have been analyzed for a direct-coupled turbojet engine. Control parameters for various conditions of engine operation are discussed. A hypothetical engine control is presented to illustrate the use of these parameters. An adjustable speed governor was found to offer a desirable method of over-all engine control. The selection of a minimum value of fuel flow was found to offer a means of preventing unstable burner operation during steady-state operation. Until satisfactory high-temperature-measuring devices are developed, air-fuel ratio is considered to be a satisfactory acceleration-control parameter for the attainment of the maximum acceleration rates consistent with safe turbine temperatures. No danger of unstable burner operation exists during acceleration if a temperature-limiting acceleration control is assumed to be effective. Deceleration was found to be accompanied by the possibility of burner blow-out even if a minimum fuel-flow control that prevents burner blow-out during steady-state operation is assumed to be effective. Burner blow-out during deceleration may be eliminated by varying the value of minimum fuel flow as a function of compressor-discharge pressure, but in no case should the fuel flow be allowed to fall below the value required for steady-state burner operation.
Contributing Partner: UNT Libraries Government Documents Department
An Analysis of the Full-Floating Journal Bearing

An Analysis of the Full-Floating Journal Bearing

Date: January 28, 1947
Creator: Shaw, M.C. & Nussdorfer, T.J.
Description: An analysis of the operating characteristics of a full-floating bearing - a bearing in which a floating sleeve is located between the journal and bearing surfaces - is presented together with charts - from which the performance of such bearings may be predicted. Examples are presented to illustrate the use of these charts and a limited number of experiments conducted upon a glass full-floating bearing to verify some results of the analysis are reported. The floating sleeve can operate over a wide range of speeds for a given shaft speed, the exact value depending principally upon the ratio of clearances and upon the ratio of radii of the bearing. Lower operating temperatures at high rotative speeds are to be expected by using a full-floating bearing. This lower operating temperature would be obtained at the expense of the load-carrying capacity of the bearing if, for comparison, the clearances remain the same in both bearings. A full-floating bearing having the same load capacity as a conventional journal bearing may be designed if decreased clearances are allowable.
Contributing Partner: UNT Libraries Government Documents Department
Performance of Compressor of XJ-41-V Turbojet Engine II - Static-Pressure Ratios and Limitation of Maximum Flow at Equivalent Compressor Speed of 8000 rpm

Performance of Compressor of XJ-41-V Turbojet Engine II - Static-Pressure Ratios and Limitation of Maximum Flow at Equivalent Compressor Speed of 8000 rpm

Date: January 1, 1948
Creator: Dildine, Dean M. & Arthur, W. Lewis
Description: At the request of the Air Material Command, Army Air Forces, an investigation was conducted by the NACA Cleveland laboratory to determine the performance characteristics of the compressor of the XJ-41-V turbojet engine. This report is the second in a series presenting the compressor performance and analysis of flow conditions in the compressor. The static-pressure variation in the direction of flow through the compressor and the location and the cause of the maximum flow restriction at an equivalent speed of 8000 rpm are presented. After the initial runs were reported, the leading edges of the impeller blades and the diffuser surfaces were found to have been roughened by steel particles from a minor failure of auxiliary equipment. The leading edges of the impeller blades were refinished and all high spots resulting from scratches in the diffuser and the accessible parts of the vaned collector passages were removed. The initial overall performance and that obtained with the refinished blades are presented.
Contributing Partner: UNT Libraries Government Documents Department
Performance of Compressor XJ-41-V Turbojet Engine I - Preliminary Investigation at Equivalent Compressor Speed of 8000 RPM

Performance of Compressor XJ-41-V Turbojet Engine I - Preliminary Investigation at Equivalent Compressor Speed of 8000 RPM

Date: January 1, 1948
Creator: Ginsburg, Ambrose & Creagh, John W.R.
Description: At the request of the Air Material Command, Arm Air Forces, an investigation was conducted at the NACA Cleveland laboratory to determine the performance characteristics of the XJ-41-V turbojet-engine compressor. The complete compressor was mounted on a collecting chamber having an annular air-flow passage simulating the burner annulus of the engine and was driven by an electric motor. The compressor was extensively instrumented to determine the overall performance of the compressor, the characteristic performance of each of the compressor components, the state of the air stream in the simulated burner annulus, and the operation of the compressor bearings. An initial investigation at an equivalent compressor speed of 8000 rpm was made to determine the performance of the compressor and the collecting chamber and to determine the similarity of the air stream at the entrance to the simulated burner annulus. The mechanical performance of the compressor over a range of actual compressors speeds from 3300 to 8000 rpm is reported.
Contributing Partner: UNT Libraries Government Documents Department
Design considerations for mixed-flow centrifugal compressors with high weight-flow rates per unit frontal area

Design considerations for mixed-flow centrifugal compressors with high weight-flow rates per unit frontal area

Date: March 5, 1953
Creator: Stanitz, John D
Description: An analysis is made of the factors affecting the weight-flow rate per unit frontal area of centrifugal compressors with axial-flow vaned diffusers preceded by mixed-flow vaneless sections. It is shown that, for specified inlet conditions to the impeller and vaned diffuser, the weight-flow rate is increased at the expense of pressure ratio and vice versa. Charts are presented to help the designer make a satisfactory compromise between weight-flow rate and pressure ratio. Some conclusions of the investigation are : (1) Prewhirl is of negligible value in centrifugal compressors designed for high weight-flow rates.
Contributing Partner: UNT Libraries Government Documents Department
Design considerations of a condensing system for vaporized magnesium

Design considerations of a condensing system for vaporized magnesium

Date: November 30, 1955
Creator: Witzke, Walter R; Prok, George M & Keller, Thomas A
Description: The effect of the design characteristics of various condensing chambers on magnesium build-up at the chamber inlet was investigated. The condensing chambers are used in the vapor-condensation process for making magnesium slurries. A complete description of the various chamber designs and the procedure used in testing the chambers is given. The results are evaluated on the basis of clogging and total magnesium distilled per run. Orifice design was also considered.
Contributing Partner: UNT Libraries Government Documents Department
Design Data for Graphical Construction of Two-Dimensional Sharp-Edge-Throat Supersonic Nozzles

Design Data for Graphical Construction of Two-Dimensional Sharp-Edge-Throat Supersonic Nozzles

Date: December 2, 1948
Creator: Shames, Harold & Seashore, Ferris L.
Description: Design data are presented for the graphical construction of two-dimensional sharp-edge-throat supersonic nozzles of minimum length for test-section Mach numbers from 1.20 to 10.00. The method of characteristics used in the design is briefly reviewed.
Contributing Partner: UNT Libraries Government Documents Department
The design of brittle-material blade roots based on theory and rupture tests of plastic models

The design of brittle-material blade roots based on theory and rupture tests of plastic models

Date: April 6, 1953
Creator: Meyer, Andre J , Jr; Kaufman, Albert & Caywood, William C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Design factors for 4- by 8-inch ram-jet combustor

Design factors for 4- by 8-inch ram-jet combustor

Date: August 11, 1949
Creator: Male, Donald W & Cervenka, Adolph J
Description: None
Contributing 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

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

Date: September 24, 1951
Creator: Eckert, E.R.G. & Livingood, John N.B.
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.
Contributing Partner: UNT Libraries Government Documents Department
Carbon deposition of 19 fuels in an annular turbojet combustor

Carbon deposition of 19 fuels in an annular turbojet combustor

Date: February 3, 1949
Creator: Jonash, Edmund R & Wear, Jerrold D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Cascade investigation of cooling characteristics of a cast-finned air-cooled turbine blade for use in a turboprop engine

Cascade investigation of cooling characteristics of a cast-finned air-cooled turbine blade for use in a turboprop engine

Date: June 12, 1957
Creator: Stepka, Francis S; Richards, Hadley T & Hickel, Robert O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Carbon deposition from AN-F-58 fuels in a J33 single combustor

Carbon deposition from AN-F-58 fuels in a J33 single combustor

Date: June 24, 1949
Creator: Wear, Jerrold D & Douglass, Howard W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of fuel volatility on altitude starting limits of a turbojet engine

Effect of fuel volatility on altitude starting limits of a turbojet engine

Date: September 11, 1950
Creator: Wilsted, H D & Armstrong, J C
Description: The effect of fuel volatility on altitude starting limits of an axial-flow-compressor-type turbojet engine was investigated using fuels with Reid vapor pressures of 1.1 and 5.4 pounds per square inch. At flight Mach numbers from 0.40 to 0.85, the AN-F-58 fuel allowed consistent windmilling at altitudes 2000 to 8000 feet higher than was obtained with the 1.1-pound Reid vapor pressure fuel. At a flight Mach number of 0.25, ignition could not be established at any altitude with the lower-volatility fuel.
Contributing Partner: UNT Libraries Government Documents Department
Effect of fuel volatility on performance of tail-pipe burner

Effect of fuel volatility on performance of tail-pipe burner

Date: April 30, 1951
Creator: Barson, Zelmar & Sargent, Arthur F , Jr
Description: Fuels having Reid vapor pressures of 6.3 and 1.0 pounds per square inch were investigated in a tail-pipe burner on an axial-flow-type turbojet engine at a simulated flight Mach number of 0.6 and altitudes from 20,000 to 45,000 feet. With the burner configuration used in this investigation, having a mixing length of only 8 inches between the fuel manifold and the flame holder, the low-vapor-pressure fuel gave lower combustion efficiency at a given tail-pipe fuel-air ratio. Because the exhaust-nozzle area was fixed, the lower efficiency resulted in lower thrust and higher specific fuel consumption. The maximum altitude at which the burner would operate was practically unaffected by the change in fuel volatility.
Contributing Partner: UNT Libraries Government Documents Department
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