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Identification of Foreign Objects Damaging Compressor Blades in Turbojet Engines

Description: "Damage to the compressor blades of turbojet engines due to ingestion of foreign objects is a growing problem, the solution of which has been made more difficult by the large percentage of damaging materials that have remained unknown. A rapid emission spectroscopic method was devised to identify the chemical composition of these foreign objects. Results on laboratory-prepared specimens and blades from damaged engines show that the method can be utilized to determine the nature of the ingested foreign objects" (p. 1).
Date: January 7, 1957
Creator: Spakowski, A. E. & Graab, J.
Partner: UNT Libraries Government Documents Department

Bonded lead monoxide films as solid lubricants for temperatures up to 1250 degrees F

Description: Report presenting a friction, wear, and endurance-lift study made with bonded films of mixed oxides containing lead monoxide (PbO) as the main component. The coatings lubricated over the entire temperature range, but were far more effective from 500 to 1250 degrees Fahrenheit than at the lower temperatures. Results regarding the effect of silica additions on coating formation, determination of coating composition, effect of coating thickness on friction and wear, effect of temperature on friction and wear, and endurance properties are provided.
Date: May 7, 1957
Creator: Sliney, Harold E. & Johnson, Robert L.
Partner: UNT Libraries Government Documents Department

Investigation of boundary-layer transition on flat-faced bodies of revolution at high supersonic speeds

Description: An experimental investigation was carried out to determine the boundary-layer transition characteristics of bodies of revolution with flat and nearly flat faces. Shadowgraphs indicated that the boundary layer remained laminar on the front faces and was turbulent only on the sides. The tests also yielded information on the total drag coefficients and static longitudinal stability of the models.
Date: June 7, 1957
Creator: Canning, Thomas N. & Sommer, Simon C.
Partner: UNT Libraries Government Documents Department

Analysis of coolant flow and pressure requirements for a return-flow turbine rotor blade design using hydrogen, helium, or air as coolant

Description: From Introduction: "This report presents the results of an analysis to determine the coolant flow and pressure requirements for a particular return-flow turbine rooter blade design utilizing hydrogen, helium, or air as the coolant."
Date: May 7, 1957
Creator: Slone, Henry O. & Donoughe, Patrick L.
Partner: UNT Libraries Government Documents Department

An Analysis of Vertical-Tail Loads Measured in Flight on a Swept-Wing Bomber Airplane

Description: From Introduction: "This paper presents results of an analysis of shear, bending-moment, and torque loads measured on the vertical tail during rudder-step, rudder-pulse, aileron-roll, and steady-sideslip maneuvers. In order to assess effects of Mach number and altitude, the maneuvers were performed at altitudes of 15,000, 25,000, and 35,000 feet and Mach numbers from 0.49 to 0.82."
Date: May 7, 1957
Creator: McGowan, William A. & Cooney, T. V.
Partner: UNT Libraries Government Documents Department

Performance of an impulse-type supersonic-compressor rotor having a mean turning of 114 degrees

Description: Report presenting testing of the performance of a 16-inch tip-diameter rotor designed for impulse operation at the mean radius with a relative Mach number of 1.53 and 114 degrees of turning. Results regarding the rotor with guide vanes, blade-element performance, rotor alone, and modified rotor hub contour are provided.
Date: January 7, 1957
Creator: Goldberg, Theodore J. & Erwin, John R.
Partner: UNT Libraries Government Documents Department

Recent Data on Tire Friction During Landing

Description: "An investigation was made at the Langley landing-loads track to obtain data on the coefficient of friction during wheel spin-up. A landing gear was tested at horizontal velocities ranging from 0 to 180 feet per second together with vertical velocities of 7.0 and 9.3 feet per second. The results indicate the effect of forward speed and tire inflation pressure on the coefficient of friction" (p. 1).
Date: June 7, 1957
Creator: Batterson, Sidney A.
Partner: UNT Libraries Government Documents Department

Experimental Investigation of a Five-Stage Axial-Flow Research Compressor with Transonic Rotors in All Stages 4: Blade-Element Performance

Description: Memorandum presenting the detailed blade-element performance of a five-stage axial-flow compressor for analysis purposes as well as to provide a contribution to the growing body of information necessary for continuing improvement in designing compressors. Results regarding overall and stage performance, blade-element performance, rotor blade-element performance, stator blade-element performance, comparison with design, consideration of boundary-layer blockage effects, and solution of equilibrium equation are provided.
Date: May 7, 1957
Creator: Sandercock, Donald M.
Partner: UNT Libraries Government Documents Department

Hinge-Moment and Effectiveness Characteristics of an Aspect-Ratio-8.2 Flap-Type Control on a 60 Degree Delta Wing at Mach Numbers from 0.72 to 1.96

Description: Memorandum presenting an investigation of a semispan-wing-fuselage model with a 60 degree delta wing with an aspect-ratio-8.2 blunt trailing-edge flap-type control in the 9- by 12-inch blowdown tunnel. Control hinge-moment and effectiveness characteristics were obtained over an angle-of-attack range of plus or minus 10 degrees at control deflections up to 90 degrees.
Date: January 7, 1957
Creator: Guy, Lawrence D.
Partner: UNT Libraries Government Documents Department

Measurements of Runway Roughness of Four Commercial Airports

Description: "Measurements of runway roughness were made on runaways at Washington National Airport, New York International Airport, La Guardia Airport, and Logan International Airport, Boston, Mass. This report presents these measurements in the form of tables as well as plots" (p. 1).
Date: January 7, 1957
Creator: Potter, Dexter M.
Partner: UNT Libraries Government Documents Department

Brief Studies of Turbojet Combustor and Fuel-System Operation With Hydrogen Fuel at -400 Degrees F

Description: Memorandum presenting a single J33 combustor and an experimental tubular combustor incorporating a fuel vaporizer as operated with gaseous hydrogen at temperatures slightly above the boiling point of the fuel. Data were obtained to explore possible effects of the fuel temperature on combustor performance and on the control and measurement of fuel flow.
Date: March 7, 1957
Creator: Straight, David M.; Smith, Arthur L. & Christenson, Harold H.
Partner: UNT Libraries Government Documents Department