100 Areas: (For technical progress letter No. 104), June 25--July 1 (open access)

100 Areas: (For technical progress letter No. 104), June 25--July 1

None
Date: July 5, 1946
Creator: Jordan, W. E.
Object Type: Report
System: The UNT Digital Library
100 Areas: (For Technical Progress Letter No. 107), July 16--22 (open access)

100 Areas: (For Technical Progress Letter No. 107), July 16--22

This technical progress report details 100 Area activities for the time period of July 16 through July 22, 1946.
Date: July 26, 1946
Creator: Jordan, W. E.
Object Type: Report
System: The UNT Digital Library
100 Areas technical activities report -- Engineering, June, 1948 (open access)

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

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 slugs.
Date: July 19, 1948
Creator: Woods, W. K.
Object Type: Report
System: The UNT Digital Library
100 Areas technical progress letter No. 105, July 2--July 8 (open access)

100 Areas technical progress letter No. 105, July 2--July 8

The physics of the shutdown of the D pile on July 2 is emphasized in the operation report. The F pile shutdown and operating specifics are also discussed. Water, corrosion, and engineering are reported for the B, D, and F areas.
Date: July 12, 1946
Creator: Jordan, W. E.
Object Type: Report
System: The UNT Digital Library
234-5 Project ventilation specifications (open access)

234-5 Project ventilation specifications

This brief memo from the 300 area of the Hanford plant, July 13, 1948, describes the need to redesign the ventilation system so as to minimize hazards associated with performing maintenance work.
Date: July 13, 1948
Creator: Work, J.B.
Object Type: Report
System: The UNT Digital Library
234-5 status reports (open access)

234-5 status reports

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.
Object Type: Report
System: The UNT Digital Library
291-T Emergency Exhaust Air Scrubbers (open access)

291-T Emergency Exhaust Air Scrubbers

None
Date: July 16, 1948
Creator: Stainken, F. A. R.
Object Type: Report
System: The UNT Digital Library
Abstracts Pertaining to Seaplanes (open access)

Abstracts Pertaining to Seaplanes

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.
Object Type: Report
System: The UNT Digital Library
Acute Radiotoxicity of Injected Yttrium91 (open access)

Acute Radiotoxicity of Injected Yttrium91

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.
Object Type: Report
System: The UNT Digital Library
Aerial photography. (open access)

Aerial photography.

A training manual designed to teach aerial photography for military purposes.
Date: July 8, 1941
Creator: United States. War Department.
Object Type: Book
System: The UNT Digital Library
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 (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

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.
Object Type: Report
System: The UNT Digital Library
Aerodynamic Characteristics of Several Modifications of a 0.45-Scale Model of the Vertical Tail of the Curtiss XP-62 Airplane (open access)

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

"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.
Object Type: Report
System: The UNT Digital Library
Aerodynamic Properties of Slender Wing-Body Combinations at Subsonic, Transonic, and Supersonic Speeds (open access)

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

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.
Object Type: Report
System: The UNT Digital Library
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 (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

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.
Object Type: Report
System: The UNT Digital Library
Airfoil-Contour Modifications Based on (Epsilon)-Curve Method of Calculating Pressure Distribution (open access)

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

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
Object Type: Report
System: The UNT Digital Library
Airspeed Fluctuations as a Measure of Atmospheric Turbulence (open access)

Airspeed Fluctuations as a Measure of Atmospheric Turbulence

"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.
Object Type: Report
System: The UNT Digital Library
Alpha Particles from Fission as Recorded by Photographic Emulsions (open access)

Alpha Particles from Fission as Recorded by Photographic Emulsions

None
Date: July 1, 1948
Creator: Marshall, L
Object Type: Report
System: The UNT Digital Library
Altitude Performance of AN-F-58 Fuels in British Rolls-Royce Nene Single Combustor (open access)

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

"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 feet, engine speeds from 40- to 100- percent normal rated, and flight Mach numbers of 0.0 and 0.6" (p. 1).
Date: July 8, 1949
Creator: Cook, William P. & Koch, Richard G.
Object Type: Report
System: The UNT Digital Library
Altitude-Test-Chamber Investigation of a Solar Afterburner on the 24C Engine 1 - Operational Characteristics and Altitude Limits (open access)

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

"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 maximum fuel-air ratio of the afterburner, as limited by maximum permissible turbine-discharge gas temperatures at rated engine speed, varied between 0.0295 and 0.0380 over a range of flight Mach numbers from 0.25 to 1.0 and at altitudes of 20,000 and 30,000 feet" (p. 1).
Date: July 6, 1948
Creator: Dowman, Harry W. & Reller, John O.
Object Type: Report
System: The UNT Digital Library
Aluminum-Zinc-Magnesium-Copper Casting Alloys (open access)

Aluminum-Zinc-Magnesium-Copper Casting Alloys

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.
Object Type: Report
System: The UNT Digital Library
Analysis of Heat and Compressibility Effects in Internal Flow Systems and High-Speed Tests of a Ram-Jet System (open access)

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

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.
Object Type: Report
System: The UNT Digital Library
Analysis of Jet-Propulsion-Engine Combustion-Chamber Pressure Losses (open access)

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

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
Object Type: Report
System: The UNT Digital Library
An analysis of life expectancy of airplane wings in normal cruising flight (open access)

An analysis of life expectancy of airplane wings in normal cruising flight

From Summary: "The independent variables considered in the analysis included stress-concentration factor, stress-load relation, wing loading, design and cruising speeds, design gust velocity, and airplane size. Several methods for estimating fatigue life from gust frequencies are discussed."
Date: July 1945
Creator: Putnam, Abbott A.
Object Type: Report
System: The UNT Digital Library
Analysis of propeller efficiency losses associated with heated-air thermal de-icing (open access)

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

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.
Object Type: Report
System: The UNT Digital Library