This system will be undergoing maintenance Tuesday, December 6 from 9AM to 12PM CST.

  You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Effect of nozzle secondary flows on turbine performance as indicated by exit surveys of a rotor

Effect of nozzle secondary flows on turbine performance as indicated by exit surveys of a rotor

Date: April 15, 1954
Creator: Whitney, Warren, J; Buckner, Howard A , Jr & Monroe, Daniel E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of oil flow to piston on piston-ring sticking and oil consumption in a single-cylinder engine

Effect of oil flow to piston on piston-ring sticking and oil consumption in a single-cylinder engine

Date: May 1, 1945
Creator: Meigs, John B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental determination of gas motion accompanying screeching combustion in a 6-inch simulated afterburner

Experimental determination of gas motion accompanying screeching combustion in a 6-inch simulated afterburner

Date: December 4, 1953
Creator: Blackshear, Perry L; Rayle, Warren D & Tower, Leonard K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental Determination of Linear Dynamics of Two-Spool Turbojet Engines

Experimental Determination of Linear Dynamics of Two-Spool Turbojet Engines

Date: October 18, 1954
Creator: Novik, David & Heppler, Herbert
Description: Transfer functions descriptive of the response of most engine variables were determined from transient data that were obtained from approximate step inputs in fuel flow and in exhaust-nozzle area. The speed responses of both spools to fuel flow and to turbine-inlet temperature appeared as identical first-order lags. Response to exhaust-nozzle area was characterized by a first-order lag response of the outer-spool speed, accompanied by virtually no change in inner-spool speed.
Contributing Partner: UNT Libraries Government Documents Department
Experimental Determination of Thermal Conductivity of Low-Density Ice

Experimental Determination of Thermal Conductivity of Low-Density Ice

Date: March 1, 1954
Creator: Coles, Willard D.
Description: The thermal conductivity of low-density ice has been computed from data obtained in an experimental investigation of the heat transfer and mass transfer by sublimation for an iced surface on a flat plate in a high-velocity tangential air stream. The results are compared with data from several sources on the thermal conductivity of packed snow and solid glaze ice. The results show good agreement with the equations for the thermal conductivity of packed snow as a function of snow density. The agreement of the curves for packed snow near the solid ice regime with the values of thermal conductivity, of ice indicates that the curves are applicable over the entire-ice-density range.
Contributing Partner: UNT Libraries Government Documents Department
Experimental determination of time constants and Nusselt numbers for bare-wire thermocouples in high-velocity air streams and analytic approximation of conduction and radiation errors

Experimental determination of time constants and Nusselt numbers for bare-wire thermocouples in high-velocity air streams and analytic approximation of conduction and radiation errors

Date: January 1, 1952
Creator: Scadron, Marvin D & Warshasky, Isidore
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental Droplet Impingement on Several Two-Dimensional Airfoils with Thickness Ratios of 6 to 16 Percent

Experimental Droplet Impingement on Several Two-Dimensional Airfoils with Thickness Ratios of 6 to 16 Percent

Date: December 1, 1956
Creator: Gelder, Thomas F.; Smyers, William H., Jr. & VonGlahn, Uwe
Description: The rate and area of cloud droplet impingement on several two-dimensional swept and unswept airfoils were obtained experimentally in the NACA Lewis icing tunnel with a dye-tracer technique. Airfoil thickness ratios of 6 to 16 percent; angles of attack from 0 deg to 12 deg, and chord sizes from 13 to 96 inches were included in the study. The data were obtained at 152 knots and are extended to other conditions by dimensionless impingement parameters. In general, the data show that the total and local collection efficiencies and impingement limits are primary functions of the modified inertia parameter (in which airspeed, droplet size, and body size are the most significant variables) and the airfoil thickness ratio. Local collection efficiencies and impingement limits also depend on angle of attack. Secondary factors affecting impingement characteristics are airfoil shape, camber, and sweep angle. The impingement characteristics obtained experimentally for the airfoils were within +/-10 percent on the average of the characteristics calculated from theoretical trajectories. Over the range of conditions studied, the experimental data demonstrate that a specific method can be used to predict the impingement characteristics of swept airfoils with large aspect ratios from the data for unswept airfoils of the same ...
Contributing Partner: UNT Libraries Government Documents Department
Experimental evaluation by thermodynamic methods of work input to a centrifugal compressor operating with water injection

Experimental evaluation by thermodynamic methods of work input to a centrifugal compressor operating with water injection

Date: January 12, 1951
Creator: Kovach, Karl; Beede, William L & Hamrick, Joseph T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental Droplet Impingement on Four Bodies of Revolution

Experimental Droplet Impingement on Four Bodies of Revolution

Date: December 1, 1957
Creator: Lewis, James P. & Ruggeri, Robert S.
Description: The rate and. area of cloud droplet impingement on four bodies of revolution were obtained experimentally in the NACA Lewis icing tunnel with a dye-tracer technique. The study included spheres, ellipsoidal forebodies of fineness ratios of 2.5 and 3.0, and a conical forebody of 300 included angle and covered a range of angles of attack from 0? to 60 and rotational speeds up to 1200 rpm. The data were obtained at an airspeed of 157 knots and are correlated by dimensionless impingement parameters. In general, the experimental data show that the local and total impingement rates and impingement limits of bodies of revolution are primarily functions of the modified inertia parameters, the body shape, and fineness ratio. Both the local impingement rate and impingement limits depend upon the angle of attack. Rotation of the bodies had a negligible effect on the impingement characteristics except for an averaging effect at angle of attack. For comparable diameters the bluffer bodies had the largest total impingement efficiency, but the finer and sharper bodies had the largest values of maximum local impingement efficiency and, in most cases, the largest limits of impingement. In most cases, the impingement characteristics were less than those calculated from ...
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of a 0.4 hub-tip diameter ratio axial-flow compressor inlet stage at transonic inlet relative Mach numbers II : stage and blade-element performance

Experimental investigation of a 0.4 hub-tip diameter ratio axial-flow compressor inlet stage at transonic inlet relative Mach numbers II : stage and blade-element performance

Date: January 10, 1955
Creator: Montgomery, John C & Glaser, Frederick W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of a 7-inch-tip-diameter transonic turbine

Experimental investigation of a 7-inch-tip-diameter transonic turbine

Date: January 16, 1958
Creator: Whitney, Warren J & Wintucky, William T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of a 0.4 hub-tip diameter ratio axial-flow compressor inlet stage at transonic inlet relative Mach numbers III : effect of tip taper on over-all and blade-element performances

Experimental investigation of a 0.4 hub-tip diameter ratio axial-flow compressor inlet stage at transonic inlet relative Mach numbers III : effect of tip taper on over-all and blade-element performances

Date: March 30, 1956
Creator: Montgomery, John C & Glaser, Frederick
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of a 16-inch impulse-type supersonic-compressor rotor

Experimental investigation of a 16-inch impulse-type supersonic-compressor rotor

Date: October 5, 1951
Creator: Ullman, Guy N; Hartmann, Melvin J & Tysl, Edward R
Description: Performance data and characteristics of a 16-inch impulse-type supersonic-compressor rotor are presented. The experimental portion of this investigation was conducted in Freon-12. A peak pressure ratio of 3.6 was obtained with an adiabatic efficiency of 0.80 at design conditions. Performance was continuous from impulse operation, at open throttle, to shock-in-rotor operation at the stall condition.
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of air-cooled turbine blades in turbojet engine IX : evaluation of the durability of noncritical rotor blades in engine operation

Experimental investigation of air-cooled turbine blades in turbojet engine IX : evaluation of the durability of noncritical rotor blades in engine operation

Date: December 5, 1951
Creator: Stepka, Francis S & Hickel, Robert O
Description: The durability of five different structural or cooling configurations or combination of both of air-cooled blades made of noncritical materials was investigated in a modified turbojet engine. The greater part of the investigation was conducted at an engine speed of 11,500 rpm, a turbine-inlet temperature of approximately 1670 degrees F, and a cooling-air to combustion gas flow ratio per blade of 0.05. The results of the investigation indicated that air-cooled blades made of noncritical metals can be operated for extended periods of time in engines at current inlet temperatures; however, before these blades are considered completely satisfactory for gas-turbine application, some means such as coatings is required to inhibit the oxidation of the blades.
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of air-cooled turbine blades in turbojet engine XI : internal-strut-supported rotor blade

Experimental investigation of air-cooled turbine blades in turbojet engine XI : internal-strut-supported rotor blade

Date: June 2, 1952
Creator: Cochran, Reeves P; Stepka, Francis S & Krasner, Morton H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of a lightweight rocket chamber

Experimental investigation of a lightweight rocket chamber

Date: October 1, 1956
Creator: Dalgleish, John E & Tischler, Adelbert O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of a surge control on a turbojet engine

Experimental investigation of a surge control on a turbojet engine

Date: November 18, 1955
Creator: Novik, David; Heppler, Herbert & Stiglic, Paul M
Description: The action of a surge control that reduced fuel flow after receiving an indication of surge initiation was investigated. The control system could successfully limit surge to only 1 cycle but could not completely eliminate surge. Inability to interrupt a surge cycle before its completion was attributed to the conclusion that a surge cycle is irreversible.
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of a five-stage axial-flow research compressor with transonic rotors in all stages IV : blade-element performance

Experimental investigation of a five-stage axial-flow research compressor with transonic rotors in all stages IV : blade-element performance

Date: May 7, 1957
Creator: Sandercock, Donald M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of a high subsonic Mach number turbine having low rotor suction-surface diffusion

Experimental investigation of a high subsonic Mach number turbine having low rotor suction-surface diffusion

Date: October 10, 1956
Creator: Hauser, Cavour H & Nusbaum, William J
Description: The quasi-three-dimensional method for the aerodynamic design of both stator and rotor blades is presented for a turbine having high weight flow and high specific work output. The turbine was designed for a relative critical velocity ratio of 0.82 at the rotor hub inlet. At the condition of equivalent design work output and blade speed, the efficiency based on the overall actual total-pressure ratio was 0.875, which is almost at high as those obtained for conservatively designed turbines.
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of a transonic compressor rotor with a 1.5-inch chord length and an aspect ratio of 3.0 I : design, over-all performance, and rotating-stall characteristics

Experimental investigation of a transonic compressor rotor with a 1.5-inch chord length and an aspect ratio of 3.0 I : design, over-all performance, and rotating-stall characteristics

Date: March 28, 1955
Creator: Tysl, Edward R; Schwenk, Francis C & Watkins, Thomas B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of a transonic axial-flow-compressor rotor with double-circular-arc airfoil blade sections II : blade-element performance

Experimental investigation of a transonic axial-flow-compressor rotor with double-circular-arc airfoil blade sections II : blade-element performance

Date: January 10, 1955
Creator: Lewis, George W , Jr & Schwenk, Francis C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of a transonic compressor rotor with a 1.5-inch chord length and an aspect ratio of 3.0 II : blade-element performance

Experimental investigation of a transonic compressor rotor with a 1.5-inch chord length and an aspect ratio of 3.0 II : blade-element performance

Date: August 18, 1955
Creator: Schwenk, Francis C & Tysl, Edward R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of a two-dimensional split-wing ram-jet inlet at Mach number of 3.85

Experimental investigation of a two-dimensional split-wing ram-jet inlet at Mach number of 3.85

Date: August 11, 1952
Creator: Connors, James F & Woollett, Richard R
Description: Performance characteristics of a two-dimensional isentropic diffuser have been experimentally determined at a Mach number of 3.85. At zero angle of attack, a maximum total-pressure recovery of 0.41 was obtained with a supercritical mass-flow ratio of 0.95. As a consequence of the twin-duct arrangement of the diffuser, a large discontinuity in pressure recovery and mass flow with a characteristic hysteresis was encountered between critical and subcritical operation. An asymmetric shock pattern with large-scale separation and flow reversal in one of the passages occurred at reduced mass flows. Pressure and force data presented for an angle-of-attack range from zero to 4 degrees.
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of air-cooled turbine blade in turbojet engine VIII : rotor blades with capped leading edges

Experimental investigation of air-cooled turbine blade in turbojet engine VIII : rotor blades with capped leading edges

Date: October 18, 1951
Creator: Smith, Gordon T & Hickel, Robert O
Description: An air-cooled turbine blade with a capped leading edge was investigated in a modified commercial turbojet engine over a range of engine speed from 4000 to 11,350 rpm. The cooling performance of the caped-leading-edge configuration was superior to all leading-edge cooling modifications previously investigated.
Contributing Partner: UNT Libraries Government Documents Department