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100 Area Water Study

Description: This paper gives a cost breakdown of all the water facilities in the 100-F area for the month of January, 1948. Also given is the cost of chlorine for addition to the process water system along with where it is added and in what amounts. Lastly, the average figure for the hardness for the Columbia River water at Hanford.
Date: September 23, 1948
Creator: Beekman, S. W.
Item Type: Refine your search to only Report
open access

Additional Results in a Free-Flight Investigation of Control Effectiveness of Full-Span, 0.2-Chord Plain Ailerons at High Subsonic, Transonic, and Supersonic Speeds to Determine Some Effects of Wing Sweepback, Aspect Ratio, Taper, and Section Thickness Ratio

Description: Report discussing an aerodynamic control effectiveness study using free-flight, rocket-propelled test vehicles. Information about the effects of wing sweepback, aspect ratio, taper ratio, and section thickness ratio on the rolling effectiveness of full-span, sealed ailerons is provided.
Date: April 23, 1948
Creator: Sandahl, Carl A. & Strass, H. Kurt
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics of a 42 Degree Swept-Back Wing With Aspect Ratio 4 and NACA 64(Sub 1)-112 Airfoil Sections at Reynolds Numbers From 1,700,000 to 9,500,000

Description: Report discussing testing on a 42 degree swept-back wing to determine its low-speed aerodynamic characteristics in pitch and yaw at high Reynolds numbers. The main effect of increasing the Reynolds number was delayed wing stalling to higher angles of attack. Roughness on the wing leading edge also had a large adverse effect on lift, drag, and pitching-moment characteristics at higher Reynolds numbers.
Date: May 23, 1947
Creator: Neely, Robert H. & Conner, D. William
Item Type: Refine your search to only Report
open access

Altitude-chamber performance of British Rolls-Royce Nene II engine 1: standard 18.75-inch-diameter jet nozzle

Description: Report presenting an altitude-chamber investigation to determine the altitude performance characteristics of the British Rolls-Royce Nene II turbojet engine with a standard 18.75-inch-diameter jet nozzle. Results regarding the simulated flight performance and generalized performance across other altitude and pressure characteristics are provided.
Date: September 23, 1949
Creator: Barson, Zelmar & Wilsted, H. D.
Item Type: Refine your search to only Report
open access

Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine 1 - Analysis of Turbine Performance

Description: A wind tunnel investigation was conducted to determine the performance of a turbine operating as an integral part of a turbojet engine. Data was obtained while the engine was running over full operable range of speeds at various altitudes and flight mach numbers, and with four nozzles of different outlet areas.A maximum turbine efficiency of 0.875 was obtained at altitude of 15 thousand feet, Mach number 0.53, and corrected turbine speed of 5900 rpm.
Date: August 23, 1948
Creator: Conrad, Earl W.; Dietz, Robert O., Jr. & Golladay, Richard L.
Item Type: Refine your search to only Report
open access

Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine 2 - Analysis of Compressor Performance

Description: Compressor performance properties for two 11-stage compressors of 3000-pound-thrust axial-flow turbojet engines were determined. Data are presented for a range of simulated altitudes and a range of Mach numbers for various modifications of the engine.
Date: August 23, 1948
Creator: Dietz, Robert O., Jr.; Berdysz, Joseph J. & Howard, Ephraim M.
Item Type: Refine your search to only Report
open access

Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine 3 - Analysis of Combustion-Chamber Performance

Description: Combustion chamber performance properties of a 3000-pound-thrust axial-flow turbojet engine were determined. Data are presented for a range of simulated altitudes from 15,000 to 45,0000 feet and a range of Mach numbers from 0.23 to 1.05 for various modifications of the engine.
Date: August 23, 1948
Creator: Campbell, Carl E.
Item Type: Refine your search to only Report
open access

Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, 4, Operational Characteristics

Description: An investigation was conducted to evaluate the operational characteristics of a 3000 pound thrust axial flow turbojet engine over a range of simulated altitudes from 2000 to 50,000 feet and simulated flight Mach numbers from 0 to 1.04 throughout the operable range of engine speeds. Engine operating range, acceleration, deceleration, starting, altitude, and flight Mach number compensation of the fuel control system, and operation of the lubrication system at high and low ambient air temperatures… more
Date: August 23, 1948
Creator: Hawkins, W. Kent & Meyer, Carl L.
Item Type: Refine your search to only Report
open access

Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine, Part 5, Performance and Windmilling Drag Characteristics

Description: "An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the performance and windmilling drag characteristics of an original and a modified turbojet engine of the same type. Data have been obtained at simulated altitudes from 5000 to 45,000 feet, simulated flight Mach numbers from 0.09 to 1.08, and engine speeds from 4000 to 12,500 rpm. Engine performance data are presented for both engines to show the effects of altitude at a flight Mach number of 0.25 and of… more
Date: August 23, 1948
Creator: Meyer, Carl L. & Bloomer, Harry E.
Item Type: Refine your search to only Report
open access

Altitude-wind-tunnel investigation of operational characteristics of Westinghouse X24C-4B axial flow turbojet engine

Description: From Summary: "An investigation has been conducted in the NACA Cleveland altitude wind tunnel to evaluate the operational characteristics of a 3000-pound-thrust axial-flow turbojet engine over a range of simulated altitudes from 2000 to 50,000 feet and simulated flight Mach numbers from 0 to 1.04 throughout the operable range of engine speeds. Operational characteristics investigated include engine operating range, acceleration, deceleration, starting, altitude and flight-Mach-number compensati… more
Date: November 23, 1948
Creator: Hawkins, W. Kent & Meyer, Carl L.
Item Type: Refine your search to only Report
open access

Analysis of urine samples for iron and S{sup 35}

Description: On August 21, 1948, several smear samples of contamination from the inner rod room at 100-F Area were submitted for beta identification. This contamination was spread as a result of maintenance work on the horizontal rods. Urine sample were deemed advisable for two men who had been exposed while working on the rods. These urine samples were also submitted for beta analyses. The analyses of the smears showed the contamination to consist of primarily S{sup 35} (65%) and Fe{sup 59} (30%)and minor … more
Date: November 23, 1948
Creator: Thornburn, R. C.
Item Type: Refine your search to only Report
open access

Analytical requirements of the 234-5 Project

Description: At this time it is desirable that preliminary estimates be made of the manpower, equipment, space, layout and facility requirements of the analytical section for the 234-5 Project. To arrive at these requirements a rough estimate of the required analyses, their scope and their frequency has been compiled. This is expected to serve as a basis for the Laboratories Division to outline their space and equipment requirements as soon as possible and to assemble the required personnel for operation la… more
Date: October 23, 1947
Creator: Work, J.B.
Item Type: Refine your search to only Report
open access

The Application of Tracer Techniques to the Determination of Uranium Extraction Coefficients

Description: Abstract: This report deals with the development of a method using tracer technique for determining uranium extraction coefficients on solutions of low uranium concentration. It was found that extraction coefficients could be determined on systems containing as low as one part per million uranium using 1900 level uranium as the tracer. Results of several extraction series are presented in which aluminum nitrate is used as the salting agent and dibutyl carbitol the organic extractant.
Date: January 23, 1947
Creator: Lee, D. A.; Woodard, R. W. & Clewett, G. H.
Item Type: Refine your search to only Report
open access

An approximate method for calculating the effect of surface roughness on the drag of an airplane

Description: From Summary: "A method for computing the effect of surface roughness on the drag coefficient of an airplane is presented. Calculated results using this method are compared with experimental results from both flight and wind-tunnel tests. In general, the agreement is believed satisfactory."
Date: July 23, 1947
Creator: Hall, Charles F. & Fitzgerald, Fred F.
Item Type: Refine your search to only Report
open access

The calculation of drag for airfoil sections and bodies of revolution at subcritical speeds

Description: Report presenting a method for calculating the drag, in a real compressible fluid and at subcritical Mach numbers, of airfoil sections at arbitrary life coefficients and of bodies of revolution at zero angle of attack. The values of drag coefficient are compared with values obtained for the same configurations by other methods. The differences between the results are found to lie withint he limits of accuracy of current experimental techniques.
Date: April 23, 1947
Creator: Heaslet, Max A. & Nitzberg, Gerald E.
Item Type: Refine your search to only Report
open access

Cooling Characteristics of the V-1650-7 Engine, 1, Coolant-Flow Distribution, Cylinder Temperatures, and Heat Rejections at Typical Operating Conditions

Description: From Summary: "An investigation was conducted to determine the coolant-flow distribution, the cylinder temperatures, and the heat rejections of the V-1650-7 engine . The tests were run a t several power levels varying from minimum fuel consumption to war emergency power and at each power level the coolant flows corresponded to the extremes of those likely to be encountered in typical airplane installations, A mixture of 30-percent ethylene glycol and 70-percent water was used as the coolant. T… more
Date: May 23, 1947
Creator: Povolny, John H. & Bogdan, Louis J.
Item Type: Refine your search to only Report
open access

Derivation of charts for determining the horizontal tail load variation with any elevator motion

Description: From Summary: "The equations relating the wing and tail loads are derived for a unit elevator displacement. These equations are then converted into a nondimensional form and charts are given by which the wing- and tail-load-increment variation may be determined under dynamic conditions for any type of elevator motion and for various degrees of airplane stability. In order to illustrate the use of the charts, several examples are included in which the wing and tail loads are evaluated for a numb… more
Date: November 23, 1942
Creator: Pearson, Henry A.
Item Type: Refine your search to only Report
open access

The Determination of Thorium in Uranium-Thorium Alloys, Using Cupferron

Description: Technical report describing that the use of controlled amounts of carbonate, acting both as complexing agent buffer led to a fairly satisfactory procedure for the determination of Th in Th-U alloys, using cupferron. The alloy, dissolved in NHO2, in the presence of HF, is treated with H2SO4 and the mixture is evaporated in SO2 fumes. The solution is diluted and (NH4)2CO2 is added. Th is precipitated from this solution with cupferron. The precipitate is weighed as ThO2 after ignition. An accura… more
Date: November 23, 1945
Creator: Eckert, A. C. & Bane, R. W.
Item Type: Refine your search to only Report
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