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Preliminary Index to Geological Survey Trace Elements Reports on Alaska for the Period January 1945-December 1952

Description: From introduction: Since 1945 the Alaskan Trace Elements Unit of the U. S. Geological. Survey has been engaged in reconnaissance for radioactive deposits in Alaska, first on behalf of the Manhattan Engineer District, later on behalf of the Atomic Energy Commission. During the period January 1945 through December 1952, 42 reports in the Survey's Trace Elements Investigations series and 18 reports in the Trace Elements Memorandum series, a totaJ of 60 reports, have been completed or are in preparation Of these 60 reports 44 have been completed and transmitted to the Commission as of December 31, 1952.
Date: February 1953
Creator: Bates, Robert Glenn

Preliminary Internal Performance Data for a Variable-Ejector Assembly on the XJ79-GE-1 Turbojet Engine, 1, Nonafterburning Configurations

Description: Internal performance of an XJ79-GE-1 variable ejector was experimentally determined with the primary nozzle in a representative nonafterburning position. Jet-thrust and air-handling data were obtained in quiescent air for 11 selected ejector configurations over a wide range of operation. Additional data, at specific operating conditions, were obtained which indicate the ejector diameter ratio for peak jet-thrust performance. The experimental ejector data are presented in both graphical and tabulated form.
Date: August 30, 1956
Creator: Greathouse, William K. & Bloomer, Harry E.

Preliminary Internal Performance Data for a Variable-Ejector Assembly on the XJ79-GE-1 Turbojet Engine, II, Afterburning Configurations

Description: Internal performance of an XJ79-GE-1 variable ejector was experimentally determined with the primary nozzle in two representative after-burning positions. Jet-thrust and air-handling data were obtained in quiescent air for 4 selected ejector configurations over a wide range of secondary to primary airflow ratios and primary-nozzle pressure ratios. The experimental ejector data are presented in both graphical and tabulated form.
Date: July 30, 1957
Creator: Bloomer, Harry E. & Groesbeck, Donald E.

Preliminary Investigation in the NACA Low-Turbulence Tunnel of Low-Drag Airfoil Sections Suitable for Admitting Air at the Leading Edge

Description: An investigation was carried out in the NACA low-turbulence tunnel to develop low-drag airfoil sections suitable for admitting air at the leading edge. A thickness distribution having the desired type of pressure distribution was found from tests of a flexible model. Other airfoil shapes were derived from this original shape by varying the thickness, the camper, the leading-edge radius, and the size of the leading-edge opening. Data are presented giving the characteristics of the airfoil shapes in the range of lift coefficients for high-speed and cruising flight. Shapes have been developed which show no substantial increases in drag over that of the same position along the chord. Many of these shapes appear to have higher critical compressibility speeds than plain airfoils of the same thickness. Low-drag airfoil sections have been developed with openings in the leading edge as large as 41.5 percent of the maximum thickness. The range of lift coefficients for low drag in several cases is nearly as large as that of the corresponding plain airfoil sections. Preliminary measurements of maximum lift characteristics indicate that nose-opening sections of the type herein considered may not produce any marked effects on the maximum lift coefficient.
Date: July 1, 1942
Creator: von Doenhoff, Albert E. & Horton, Elmer A.

Preliminary Investigation of a Ceramic Lining for a Combustion Chamber for Gas-Turbine Use

Description: Combustion chamber liners for gas turbines and experimental set-ups were tested for failure. A ceramic-lined test chamber was operated at fuel/air ratios up to 0.050. Thermal-shock evaluation indicated that a ceramic lining, which expands after firing, would crack but would not fall apart during operation. Refractoriness of the lining and the resistance to mechanical shock were adequate. In general, shell temperature reductions of approximately 400 deg F were effected by the use of this lining at fuel/air ratios of 0.016 and 0.050. The mechanism of failure of the ceramic lining was induced by sudden heating and cooling during operation.
Date: April 12, 1948
Creator: Woodward, William H & Bobrowsky, A R

Preliminary investigation of a conical spike inlet in combination with a vertical-wedge auxiliary inlet at Mach number 1.9

Description: Pressure-recovery characteristics of a nacelle-type-spike inlet in combination with a vertical-wedge auxiliary scoop are presented for a free-stream Mach number of 1.9 at zero angle of attack. The auxiliary scoop provided 17 percent additional air flow with a drop in critical pressure recovery from 0.86 to 0.81. However, in terms of inlet-engine matching, the pressure recovery of the undersized spike inlet operating at a specified corrected air flow increased with the scoop open, for example, from 0.69 to 0.81.
Date: September 27, 1955
Creator: Beke, Andrew; Allen, John L & Williams, Thomas