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Flight Investigation of a 20-Inch-Diameter Steady-Flow Ram Jet

Flight Investigation of a 20-Inch-Diameter Steady-Flow Ram Jet

Date: January 14, 1948
Creator: Disher, John H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Further measurements of intensity, scale, and spectra of turbulence in a subsonic jet

Further measurements of intensity, scale, and spectra of turbulence in a subsonic jet

Date: October 1, 1956
Creator: Laurence, James C & Stickney, Truman M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Friction and wear investigation of molybdenum disulfide II : effects of contaminants and method of application

Friction and wear investigation of molybdenum disulfide II : effects of contaminants and method of application

Date: March 1, 1954
Creator: Peterson, Marshall B & Johnson, Robert L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flame velocities of four alkylsilanes

Flame velocities of four alkylsilanes

Date: March 9, 1951
Creator: Gerstein, Melvin; Wong, Edgar L & Levine, Oscar
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-convection effects on heat transfer for turbulent flow through a vertical tube

Free-convection effects on heat transfer for turbulent flow through a vertical tube

Date: December 1, 1955
Creator: Eckert, E R G; Diaguila, Anthony J & Livingood, John N B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-flight performance of 16-inch-diameter supersonic ram-jet units I : four units designed for combustion-chamber-inlet Mach number of 0.12 at free-stream Mach number of 1.6 (units A-2, A-3, A-4, and A-5)

Free-flight performance of 16-inch-diameter supersonic ram-jet units I : four units designed for combustion-chamber-inlet Mach number of 0.12 at free-stream Mach number of 1.6 (units A-2, A-3, A-4, and A-5)

Date: September 22, 1949
Creator: Carlton, William W & Messing, Wesley E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99 IV : conical-spike external-internal compression inlet utilizing perforated cowl

Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99 IV : conical-spike external-internal compression inlet utilizing perforated cowl

Date: March 28, 1951
Creator: Madden, Robert T & Kremzier, Emil
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99 V : analysis and comparison on basis of ram-jet aircraft range and operational characteristics

Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99 V : analysis and comparison on basis of ram-jet aircraft range and operational characteristics

Date: September 13, 1951
Creator: Howard, E; Luidens, R W & Allen, J L
Description: Performance of four experimentally investigated axially symmetric spike-type nose inlets is compared on basis of ram-jet-engine aircraft range and operational problems. At design conditions, calculated peak engine efficiencies varied 25 percent from the highest value which indicates importance of inlet design. Calculations for a typical supersonic aircraft indicate possible increase in range if engine is flown at moderate angle of attack and result in engine lift utilized. For engines with fixed exhaust nozzle, propulsive thrust increases with increasing heat addition in subcritical flow region in spite of increasing additive drag. For the perforated inlet there is a range of increasing total-temperature ratios in subcritical flow region that does not yield an increase in propulsive thrust. Effects of inlet characteristics on speed stability of a typical aircraft for three types of fuel control is discussed.
Contributing Partner: UNT Libraries Government Documents Department
Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99 I : conical spike all-external compression inlet with subsonic cowl lip

Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99 I : conical spike all-external compression inlet with subsonic cowl lip

Date: January 19, 1951
Creator: Esenwein, Fred T & Valerino, Alfred S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99 III : conical-spike all-external-compression inlet with supersonic cowl lip

Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99 III : conical-spike all-external-compression inlet with supersonic cowl lip

Date: February 14, 1951
Creator: Weinstein, Maynard I & Davids, Joseph
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Expressions for measuring the accuracy of approximate solutions to compressible flow through cascades of blades with examples of use

Expressions for measuring the accuracy of approximate solutions to compressible flow through cascades of blades with examples of use

Date: October 1, 1951
Creator: Sinnette, John T; Costello, George R & Cummings, Robert L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Extension of boundary-layer heat-transfer theory to cooled turbine blades

Extension of boundary-layer heat-transfer theory to cooled turbine blades

Date: August 11, 1950
Creator: Brown, W Byron & Donoughe, Patrick L
Description: An equation for average heat transfer of a surface was derived when the boundary layer changed from laminar to turbulent. Influences on the heat transfer through a laminar boundary layer of Mach number, temperature ratio (gas temperature divided by wall temperature), and exponents of gas-property temperature relations were shown to be relatively small for air with Mach numbers less than 2 and temperature ratios between 1 and 4. Good agreement was obtained with experimental results from cylinders, an airfoil, and turbine blades.
Contributing Partner: UNT Libraries Government Documents Department
Extrapolation techniques applied to matrix methods in neutron diffusion problems

Extrapolation techniques applied to matrix methods in neutron diffusion problems

Date: July 1, 1955
Creator: Mccready, Robert R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Factors affecting laminar boundary layer measurements in a supersonic steam

Factors affecting laminar boundary layer measurements in a supersonic steam

Date: February 1, 1953
Creator: Blue, Robert E & Low, George M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-flight performance of 16-inch-diameter supersonic ram-jet units II  : five units designed for combustion-chamber-inlet Mach number of 0.16 at free-stream Mach number of 1.60 (units B-1, B-2, B-3, B-4, and B-5) /c Wesley E. Messing and Scott H. S

Free-flight performance of 16-inch-diameter supersonic ram-jet units II : five units designed for combustion-chamber-inlet Mach number of 0.16 at free-stream Mach number of 1.60 (units B-1, B-2, B-3, B-4, and B-5) /c Wesley E. Messing and Scott H. S

Date: May 5, 1950
Creator: Messing, Wesley E & Simpkinson, Scott H
Description: Free-flight performance of five 16-inch-diameter ram-jet units was determined over range of free-stream Mach numbers of 0.50 to 1.86 and gas total-temperature ratios between 1.0 and 6.1 Time histories of performance data are presented for each unit. Correlations illustrate effect of free-stream Mach number and gas total-temperature ratio on diffuser total-pressure recovery, net-thrust coefficient, and external drag coefficient. One unit had smooth steady burning throughout the entire flight and encountered a maximum free-stream Mach number of 1.86 with a net acceleration of approximately 4.2 g's.
Contributing Partner: UNT Libraries Government Documents Department
Free-flight performance of 16-inch diameter supersonic ram-jet units IV : performance of ram-jet units designed for combustion chamber inlet Mach number of 0.21 at free-stream Mach number of 1.6 over a range flight conditions

Free-flight performance of 16-inch diameter supersonic ram-jet units IV : performance of ram-jet units designed for combustion chamber inlet Mach number of 0.21 at free-stream Mach number of 1.6 over a range flight conditions

Date: February 26, 1951
Creator: Rabb, Leonard & North, Warren J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-flight performance of 16-inch-diameter supersonic ram-jet units III : four units designed for combustion-chamber-inlet Mach number of 0.245 at free-stream Mach number of 1.8 (Units D-1, D-2, D-3, and D-4)

Free-flight performance of 16-inch-diameter supersonic ram-jet units III : four units designed for combustion-chamber-inlet Mach number of 0.245 at free-stream Mach number of 1.8 (Units D-1, D-2, D-3, and D-4)

Date: June 28, 1950
Creator: Disher, John H & Rabinowitz, Leonard
Description: Performance of four 16-inch-diameter ram-jet units was determined at free-stream Mach numbers of 0.49 to 1.78 over range of gas total-temperature ratios of 1.0 to 6.1. Time histories of each flight and data on thrust, drag, diffuser efficiency, and combustion are presented. A maximum thrust coefficient of 0.88 and a maximum net acceleration of 5.13 g's were observed for the four units.
Contributing Partner: UNT Libraries Government Documents Department
Factors in selecting fuels for gas-turbine powered aircraft

Factors in selecting fuels for gas-turbine powered aircraft

Date: November 13, 1950
Creator: Gibbons, Louis C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Influence of rotor-engine torsional oscillation on control of gas-turbine engine geared to helicopter rotor

Influence of rotor-engine torsional oscillation on control of gas-turbine engine geared to helicopter rotor

Date: October 1, 1953
Creator: Sanders, John C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Influence of lubricant viscosity on operating temperatures of 75-millimeter-bore cylindrical-roller bearing at high speeds

Influence of lubricant viscosity on operating temperatures of 75-millimeter-bore cylindrical-roller bearing at high speeds

Date: February 1, 1952
Creator: Macks, Fred E; Anderson, William J & Nemeth, Zolton N
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Icing limit and wet-surface temperature variation for two airfoil shapes under simulated high-speed flight conditions

Icing limit and wet-surface temperature variation for two airfoil shapes under simulated high-speed flight conditions

Date: February 1, 1955
Creator: Coles, Willard D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Icing protection for a turbojet transport airplane : heating requirements methods of protection, and performance penalties

Icing protection for a turbojet transport airplane : heating requirements methods of protection, and performance penalties

Date: January 1, 1953
Creator: Gelder, Thomas F; Lewis, James P & Koutz, Stanley L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Influence of structure on properties of sintered chromium carbide

Influence of structure on properties of sintered chromium carbide

Date: June 1, 1952
Creator: Hamjian, H J & Lidman, W G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Influence of tube-entrance configuration on average heat-transfer coefficients and friction factors for air flowing in an Inconel tube

Influence of tube-entrance configuration on average heat-transfer coefficients and friction factors for air flowing in an Inconel tube

Date: August 23, 1950
Creator: Lowdermilk, Warren H & Grele, Milton D
Description: A heat-transfer investigation was conducted with air flowing through an electrically heated Inconel tube having either a long-approach or a right-angle-edge entrance, an inside diameter of 0.402 inch, and a length of 24 inches over a range of Reynolds numbers up to 375,000 and average inside-tube-wall temperatures up to 2000 degrees R. Good correlation of heat-transfer data was obtained for both entrances, which substantiates work previously reported. A fair correlation of friction data was obtained for both entrances. The entrance configuration had little effect on the average heat-transfer and friction coefficients.
Contributing Partner: UNT Libraries Government Documents Department