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Altitude Wind Tunnel Investigation of the Performance of Compressor, Combustor, and Turbine Components of Prototype J47D (RX1-1) Turbojet Engine

Description: As a portion of an over-all performance investigation of the prototype J47D (RX-1) turbojet engine, performance of the compressor, combustor, and turbine components has been determined in the Lewis altitude wind tunnel over a range of altitude from 5000 to 55,000 feet and at flight Mach numbers from 0.19 to 0.92. Investigations were conducted with the engine operating on an electronic control schedule and slow with a two-lever control system by which fuel flow and exhaust-nozzle area could be controlled separately. Two combustor configurations were investigated.
Date: December 21, 1951
Creator: Farley, John M.
Partner: UNT Libraries Government Documents Department

Turbine performance characteristics of a python turbine-propeller engine investigated in altitude wind tunnel

Description: Report presenting the performance of the turbine component of a Python turbine-propeller engine with four tail-pipe configurations determined over a range of altitudes, engine speeds, and fuel flows. Results regarding the corrected turbine speed, corrected turbine enthalpy drop, pressure ratio, and efficiency were established on a turbine-characteristic plot.
Date: May 1, 1951
Creator: Farley, John M. & Prince, William R.
Partner: UNT Libraries Government Documents Department

Full-scale, free-jet investigation of methods of improving outlet flow distribution in a side-inlet supersonic diffuser

Description: Report presenting a full-scale, free-jet investigation to determine the performance of a side-inlet supersonic diffuser designed for a flight Mach number of 2.75. Several internal modifications made to improve diffuser-outlet flow uniformity were also evaluated. Results regarding the general characteristics of the diffuser and effect of diffuser modifications on flow distribution are provided.
Date: March 28, 1955
Creator: Farley, John M. & Seashore, Ferris L.
Partner: UNT Libraries Government Documents Department

Preliminary performance data obtained in a full-scale, free-jet investigation of a side-inlet supersonic diffuser

Description: Report presenting an investigation of a full-scale, four-shock, side-inlet diffuser in a free-jet facility at a Mach number of 3.16. The diffuser was a heavy-duty version of the diffuser to be used with the XRJ47-W-7 engine. Results regarding the supercritical capture-area ratio, critical diffuser total-pressure recovery, and diffuser-exit flow profiles are provided.
Date: January 16, 1958
Creator: Seashore, Ferris L. & Farley, John M.
Partner: UNT Libraries Government Documents Department

Preliminary performance data obtained in a full-scale free-jet investigation of a side-inlet supersonic diffuser

Description: Report discussing an investigation into the performance of several modifications of a side-inlet ramjet engine diffuser. Total-pressure-recovery profiles, Mach number profiles, longitudinal wall static pressure distributions, and variation of the average-static to average-total pressure are presented.
Date: November 30, 1954
Creator: Farley, John M. & Smith, Ivan D.
Partner: UNT Libraries Government Documents Department

Internal Flow and Burning Characteristics of 16-inch Ram Jet Operating in a Free Jet at Mach Numbers of 1.35 and 1.73

Description: The effects of mass-flow ratio on the additive drag and normal-shock position of a single oblique-shock diffuser are presented. Also evaluated is the variation with operating condition of the velocity distribution at the combustion-chamber inlet. A comparison with connected-pipe data is included. Burner performance with a corrugated gutter-grid flame holder is discussed. It is shown that the total-pressure drop across the combustion chamber can be predicted with reasonable accuracy from the computed flame holder and combustion momentum pressure losses.
Date: May 21, 1951
Creator: Perchonok, Eugene & Farley, John M.
Partner: UNT Libraries Government Documents Department

Investigation of Conical Subsonic Diffusers for Ram-Jet Engines

Description: The efficiency of a 30 degree conical diffuser was improved as much as 20 percent and separation was eliminated by the use of vortex generators. The use of splitter cones gave only small efficiency gains, but relatively uniform diffuser-outlet velocity profiles were obtained with the better designs. A configuration which incorporated both vortex generators and a splitter cone gave efficiencies higher than those obtained with any other splitter-cone configuration and also higher than those obtained when the same vortex generators were used without the splitter cone. Moderate diffuser-efficiency increases were obtained with guide vanes; however, in all cases combustion occurred in the vane wakes.
Date: March 15, 1954
Creator: Farley, John M. & Welna, Henry J.
Partner: UNT Libraries Government Documents Department

Performance and operational characteristics of pentaborane fuel in 48-inch-diameter ram-jet engine

Description: Report presenting testing of pentaborane as a fuel in a 48-inch-diameter ram-jet engine in a free-jet facility. Each test lasted about 50 seconds and used fast-response instrumentation and prescheduled fuel-flow variation for a range of fuel-air ratios. Results regarding combustion performance, ignition, oxide deposits, and fuel-injector performance are provided.
Date: April 24, 1957
Creator: Rayle, Warren D.; Reilly, Dwight H., Jr. & Farley, John M.
Partner: UNT Libraries Government Documents Department