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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
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
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