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100 Areas technical activities report -- Engineering, June, 1948

Description: This report covers work done by the Pile Engineering Groups and work done on special assignments. Topics covered include: slug blistering and corrosion; graphite allocation to DR pile; slug molding; segmental discharge; Van Stone corrosion; flow laboratory modifications; downcomer at B pile; downcomer at D pile; annealing of pile graphite; replacement of pile atmosphere with CO{sub 2}; unit motion; beta experiment; can opening; slug annealing; new technical building, 300 area; and ruptured slug… more
Date: July 19, 1948
Creator: Woods, W. K.
Item Type: Refine your search to only Report
open access

234-5 status reports

Description: On July 14, 1949, and office memorandum was written about operations of a reprocessing building on the Hanford Site being suspended due to the mishandling of some plutonium powder. The letter describes the process of decontamination of the building surfaces, and the ventilation of the rooms of that building. It also describes the problem with the ventilation fans due to increased temperature and pressures.
Date: July 14, 1949
Creator: Lowe, W. W.
Item Type: Refine your search to only Report
open access

Abstracts Pertaining to Seaplanes

Description: Report discussing about 400 references pertaining to the hydrodynamic design of seaplanes have been compiled, and the information is presented in the form of abstracts classified under six main headings.
Date: July 24, 1947
Creator: Bidwell, Jerold M. & King, Douglas A.
Item Type: Refine your search to only Report
open access

Acute Radiotoxicity of Injected Yttrium91

Description: Report describing results of experiments that involved injecting radioactive yttrium into animals: "The excretion, retention, and distribution of the yttrium was measured, and its effect on survival and growth was observed. The average total excretion of Y91 to the time of death (from 76 hours to 24 days) was a little less than 30 per cent of the injected dose" (p. 2).
Date: July 31, 1947
Creator: Anthony, David S.
Item Type: Refine your search to only Report
open access

Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 6, taper ratio 0.6, and NACA 65A009 airfoil section

Description: From Introduction: "This paper presents the results of the investigation of the wing-alone and wing-fuselage configurations employing a wing with the quarter-chord line swept back 45^o, aspect ratio 4, taper ratio 0.3, and an NACA 65A006 airfoil section parallel to the stream."
Date: July 20, 1949
Creator: Spreemann, Kenneth P.; Morrison, William D., Jr. & Pasteur, Thomas B., Jr.
Item Type: Refine your search to only Report
open access

Aerodynamic Characteristics of Several Modifications of a 0.45-Scale Model of the Vertical Tail of the Curtiss XP-62 Airplane

Description: "In the course of an investigation to find a satisfactory vertical tail for the XP-62 airplane, a 0.45-scale vertical tail model on a stub fuselage was tested in the Langley 7- by 10-foot tunnel. This model was fitted with a flat plate to represent the horizontal tail surface. The data are presented herein for their general interest value rather than their application to this particular airplane" (p. 1).
Date: July 1946
Creator: Lowry, John G.; Turner, Thomas R. & Liddell, Robert B.
Item Type: Refine your search to only Report
open access

Aerodynamic Properties of Slender Wing-Body Combinations at Subsonic, Transonic, and Supersonic Speeds

Description: From Introduction: "In an incomprehensible medium, the mutual interference of a fuselage and wing of high-aspect ratio (to which lifting-line theory is applicable) has been treated by Lennertz, Wiselsberger, Pepper, and Multhopp in reference 1, 2, 3, and 4. It is the purpose of this note to treat the effect of on the aerodynamic loading of the mutual interference between a low-aspect-ratio pointed wing and a fuselage consisting of a slender body of revolution."
Date: July 1948
Creator: Spreiter, John R.
Item Type: Refine your search to only Report
open access

Aerodynamic Study of a Wing-Fuselage Combination Employing a Wing Swept Back 63 Degrees: Characteristics for Symmetrical Wing Sections at High Subsonic and Moderate Supersonic Mach Numbers

Description: From Summary: "Results of wind-tunnel tests are presented for a wing with the leading edge swept back 63^o and of symmetrical section in combination with a body at Mach numbers from 0.5 to 0.95 and from 1.09 to 1.51."
Date: July 7, 1949
Creator: Mas, Newton A.
Item Type: Refine your search to only Report
open access

Airfoil-Contour Modifications Based on (Epsilon)-Curve Method of Calculating Pressure Distribution

Description: From Introduction: "Certain alternations of a qualitative nature may be performed in spite of the fact that a pressure change cannot be prescribed. It is the purpose of this paper to indicate a method by which qualitative alternation may be performed. It will be noted that the present method of contour modification will serve the intended purpose of the inverse method."
Date: July 1944
Creator: Theodorsen, Theodore
Item Type: Refine your search to only Report
open access

Airspeed Fluctuations as a Measure of Atmospheric Turbulence

Description: "Increments in structural loads due to atmospheric turbulence can be accurately expressed in terms of flight speed and effective gust velocities (reference 4). Data from which the effective gust velocities could be computed were also obtained during the flights of the XC-35 airplane. These data have been used to determine the significance of the fluctuations in the pilot's indicated-airspeed readings in relation to structural loads to due to atmospheric turbulence" (p. 3).
Date: July 1945
Creator: Tolefson, H. B.
Item Type: Refine your search to only Report
open access

Altitude Performance of AN-F-58 Fuels in British Rolls-Royce Nene Single Combustor

Description: "An investigation was conducted with a single combustor from a British Rolls-Royce Nene turbojet engine to determine the altitude performance characteristics of AN-F-58 fuels. Three fuel blends conforming to AN-F-58 specifications were prepared in order to determine the influence of fuel boiling temperatures and aromatic content on combustion efficiencies and altitude operational limits. The performance of the three AN-F-58 fuels was compared in the range of altitudes from sea level to 65,000 f… more
Date: July 8, 1949
Creator: Cook, William P. & Koch, Richard G.
Item Type: Refine your search to only Report
open access

Altitude-Test-Chamber Investigation of a Solar Afterburner on the 24C Engine 1 - Operational Characteristics and Altitude Limits

Description: "An altitude-test-chamber investigation was conducted to determine the operational characteristics and altitude blow-out limits of a Solar afterburner in a 24C engine. At rated engine speed and maximum permissible turbine-discharge temperature, the altitude limit as determined by combustion blow-out occurred as a band of unstable operation of about 8000 feet altitude in width with maximum altitude limits from 32,000 feet at a Mach number of 0.3 to about 42,000 feet at a Mach number of 1.0. The … more
Date: July 6, 1948
Creator: Dowman, Harry W. & Reller, John O.
Item Type: Refine your search to only Report
open access

Aluminum-Zinc-Magnesium-Copper Casting Alloys

Description: From Introduction: "This paper contains data on the mechanical properties of sand-cast test bars having a considerable range in zinc, magnesium, and copper content and more detailed data on the properties and foundry characteristics of an aluminum-zinc-magnesium-copper alloy having a preferred composition for high strength and ductility."
Date: July 1941
Creator: Kempf, L. W.
Item Type: Refine your search to only Report
open access

Analysis of Heat and Compressibility Effects in Internal Flow Systems and High-Speed Tests of a Ram-Jet System

Description: Report discussing an analysis has been made by the NACA of the effects of heat and compressibility in the flow through the internal systems of aircraft along with equations and charts are developed whereby the flow characteristics at key stations in a typical internal system may be readily obtained.
Date: July 21, 1942
Creator: Becker, John V. & Baals, Donald D.
Item Type: Refine your search to only Report
open access

Analysis of Jet-Propulsion-Engine Combustion-Chamber Pressure Losses

Description: From Summary: "The development and the use of a chart for estimating the pressure losses in jet-engine combustion chambers are described. By means of the chart, the pressure losses due to fluid friction and to momentum changes in the air flow accompanying combustion can be separately evaluated. The over-all pressure losses computed from the pressure-loss chart are within 7 percent of the experimental values for the three types of combustion chambers considered herein."
Date: July 31, 1946
Creator: Pinkel, I. Irving & Shames, Harold
Item Type: Refine your search to only Report
open access

Analysis of propeller efficiency losses associated with heated-air thermal de-icing

Description: From Introduction: "The results of the tests made with unheated internal flow are reported in reference 1. It is the purpose of this paper to attempt to express simply the efficiency loss as a function of the parameters which govern propeller operation and the internal air flow. The derived equations are correlated with the data presented in reference 1."
Date: July 1946
Creator: Corson, Blake W. & Maynard, Julian D.
Item Type: Refine your search to only Report
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