Resource Type

States

Hanford Works monthly report, December 1950 (open access)

Hanford Works monthly report, December 1950

This is a progress report of the production reactors on the Hanford Reservation for the month of December 1950. This report takes each division (e.g., manufacturing, medical, accounting, occupational safety, security, reactor operations, etc.) of the site and summarizes its accomplishments and employee relations for that month.
Date: January 22, 1951
Creator: Prout, G. R.
Object Type: Report
System: The UNT Digital Library
Texas Attorney General Opinion: V-1145 (open access)

Texas Attorney General Opinion: V-1145

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Price Daniel, regarding a legal question submitted for clarification: Compensation of county officers in Cameron County.
Date: January 22, 1951
Creator: Texas. Attorney-General's Office.
Object Type: Text
System: The Portal to Texas History
Texas Attorney General Opinion: V-1250 (open access)

Texas Attorney General Opinion: V-1250

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Price Daniel, regarding a legal question submitted for clarification: Authority to deposit Federal funds in the State Treasury and expend such funds during the next biennium under the provisions of the general appropriation bill.
Date: August 22, 1951
Creator: Texas. Attorney-General's Office.
Object Type: Text
System: The Portal to Texas History
Texas Attorney General Opinion: V-1251 (open access)

Texas Attorney General Opinion: V-1251

Document issued by the Office of the Attorney General of Texas in Austin, Texas, providing an interpretation of Texas law. It provides the opinion of the Texas Attorney General, Price Daniel, regarding a legal question submitted for clarification: Ad valorem taxation of military housing units to be constructed and maintained on Carswell Air Force Base by private enterprise.
Date: August 22, 1951
Creator: Texas. Attorney-General's Office.
Object Type: Text
System: The Portal to Texas History
Calculations of Laminar Heat Transfer Around Cylinders of Arbitrary Cross Section and Transpiration-Cooled Walls With Application to Turbine Blade Cooling (open access)

Calculations of Laminar Heat Transfer Around Cylinders of Arbitrary Cross Section and Transpiration-Cooled Walls With Application to Turbine Blade Cooling

"An approximate method for the development of flow and thermal boundary layers in the laminar region on cylinders with arbitrary cross section and transpiration-cooled walls is obtained by the use of Karman's integrated momentum equation and an analogous heat-flow equation. Incompressible flow with constant property values throughout the boundary layer is assumed. The velocity and temperature profiles within the boundary layer are approximated by expressions composed of trigonometric functions" (p. 339).
Date: June 22, 1951
Creator: Eckert, E. R. G. & Livingood, J. N. B.
Object Type: Report
System: The UNT Digital Library
Some Effects of Spanwise Aileron Location and Wing Structural Rigidity on the Rolling Effectiveness of 0.3-Chord Flap-Type Ailerons on a Tapered Wing Having 63 Degrees Sweepback at the Leading Edge and Naca 64A005 Airfoil Sections (open access)

Some Effects of Spanwise Aileron Location and Wing Structural Rigidity on the Rolling Effectiveness of 0.3-Chord Flap-Type Ailerons on a Tapered Wing Having 63 Degrees Sweepback at the Leading Edge and Naca 64A005 Airfoil Sections

Report presenting an investigation of some effects of aileron spanwise location and wing structural rigidity on the rolling power of 0.3-chord plain, flap-type ailerons on a wing with a taper ratio of 0.25, an aspect ratio of 3.5, and swept back 63 degrees at the leading edge. Results regarding the aeroelastic effects and aileron span and spanwise location are provided.
Date: June 22, 1951
Creator: Strass, H. Kurt; Fields, E. M. & Schult, Eugene D.
Object Type: Report
System: The UNT Digital Library
Dynamic Longitudinal Stability and Control of Tandem Coupled Bomber-Fighter Airplane Models With Rigid and Pitch-Free Couplings (open access)

Dynamic Longitudinal Stability and Control of Tandem Coupled Bomber-Fighter Airplane Models With Rigid and Pitch-Free Couplings

Report presenting an investigation in the free-flight tunnel to determine the dynamic longitudinal stability and control characteristics of tandem-coupled bomber-fighter airplane models. Results regarding bomber alone tests, freely coupled combination, and rigidly coupled combination are provided.
Date: January 22, 1951
Creator: Grana, David C. & Hewes, Donald E.
Object Type: Report
System: The UNT Digital Library
Investigation of mechanisms of blade failure of forged Hastelloy B and cast Stellite 21 turbine blades in turbojet engine (open access)

Investigation of mechanisms of blade failure of forged Hastelloy B and cast Stellite 21 turbine blades in turbojet engine

An investigation was conducted to study the mechanisms of blade failure of forged Hastelloy B and cast Stellite 21. The blades were mounted in a 16-25-6 alloy rotor and subjected to 20-minute cycles consisting of 15 minutes at rated speed and approximately 5 minutes at idle. The first failures of the Hastelloy B and Stellite 21 blades were probably the result of excessive vibratory stresses and occurred after 14.25 and 16.75 hours, respectively. After 28.75 hours of operation, all but 3 of the original 25 Hastelloy B blades had either failed or contained stress-rupture-type cracks and four of the original 27 Stellite 21 blades contained stress-rupture-type cracks.
Date: August 22, 1951
Creator: Yaker, C.; Robards, C. F. & Garrett, F. B.
Object Type: Report
System: The UNT Digital Library
Effects of Reynolds Number on the Aerodynamic Characteristics of a Delta Wing at Mach Number of 2.41 (open access)

Effects of Reynolds Number on the Aerodynamic Characteristics of a Delta Wing at Mach Number of 2.41

Memorandum presenting the results of an experimental investigation to determine the effects of Reynolds number on the flow characteristics over a delta wing at a Mach number 2.41. The wing streamwise airfoil sections are based on the NACA 00-thickness series with the maximum thickness varying from 4 percent at the root section to 6.24 percent at the 90-percent spanwise station. Results regarding force data and pressure-distribution data are provided.
Date: October 22, 1951
Creator: Hatch, John E., Jr. & Hargrave, L. Keith
Object Type: Report
System: The UNT Digital Library
Investigation of Low-Speed Lateral Control and Hinge-Moment Characteristics of a 20-Percent-Chord Plain Aileron on a 47.7 Degrees Sweptback Wing of Aspect Ratio 5.1 at a Reynolds Number of 6.0 X 10(Exp 6) (open access)

Investigation of Low-Speed Lateral Control and Hinge-Moment Characteristics of a 20-Percent-Chord Plain Aileron on a 47.7 Degrees Sweptback Wing of Aspect Ratio 5.1 at a Reynolds Number of 6.0 X 10(Exp 6)

Report presenting the low-speed lateral control and hinge-moment characteristics of a 20-percent-chord plain aileron on a 47.7 degree sweptback wing of aspect ratio 5.1 in the pressure tunnel. The tests were performed with and without high-lift and stall-control devices. Results regarding the basic aileron data, rolling-moment characteristics, and pitching-moment characteristics are also provided.
Date: October 22, 1951
Creator: Hadaway, William M. & Salmi, Reino J.
Object Type: Report
System: The UNT Digital Library
Influence of airfoil trailing-edge angle and trailing-edge-thickness variation on the effectiveness of a plain flap at high subsonic Mach numbers (open access)

Influence of airfoil trailing-edge angle and trailing-edge-thickness variation on the effectiveness of a plain flap at high subsonic Mach numbers

Report presenting the effects of variation of trailing-edge angle and trailing-edge thickness on the lift characteristics of a 10-percent-chord thick symmetrical NACA airfoil section with a 25-percent-chord plain flap as determined from wind tunnel tests over a range of Mach numbers. Results regarding the section lift and pitching-moment characteristics, variation of lift coefficient with flap deflection, schileren photographs, and effect of angle of attack are provided.
Date: May 22, 1951
Creator: Hemenover, Albert D. & Graham, Donald J.
Object Type: Report
System: The UNT Digital Library
An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Force Characteristics of the Complete Configuration and Its Various Components at Mach Numbers of 1.40 and 1.59 (open access)

An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Force Characteristics of the Complete Configuration and Its Various Components at Mach Numbers of 1.40 and 1.59

Report presenting an investigation of a supersonic aircraft configuration and various combinations of its components at a range of Mach numbers. Longitudinal- and lateral-force characteristics of the configurations, as well as longitudinal- and lateral-stability derivatives, are provided.
Date: January 22, 1951
Creator: Smith, Norman F. & Marte, Jack E.
Object Type: Report
System: The UNT Digital Library
The effects on the aerodynamic characteristics of reversing the wing of a triangular wing-body combination at transonic speeds as determined by the NACA wing-flow method (open access)

The effects on the aerodynamic characteristics of reversing the wing of a triangular wing-body combination at transonic speeds as determined by the NACA wing-flow method

Testing occurred using the NACA wing-flow method at a range of Mach numbers to determine the effect on aerodynamic characteristics of reversing a triangular wing with a 6-percent-thick biconvex section. Results regarding the lift characteristics, drag characteristics, and pitching-moment characteristics are provided.
Date: October 22, 1951
Creator: McKay, James M. & Hall, Albert W.
Object Type: Report
System: The UNT Digital Library
Low-Speed Characteristics of a 45 Degree Sweptback Wing of Aspect Ratio 8 From Pressure Distributions and Force Tests at Reynolds Numbers From 1,500,000 to 4,800,000 (open access)

Low-Speed Characteristics of a 45 Degree Sweptback Wing of Aspect Ratio 8 From Pressure Distributions and Force Tests at Reynolds Numbers From 1,500,000 to 4,800,000

Report presenting an investigation of the longitudinal characteristics of a wing with 45 degree sweepback of the quarter-chord line, an aspect ratio of 8, a taper ratio of 0.45, and NACA 63(sub)1A012 airfoil sections. The results were obtained from force measurements and distribution measurements for a range of Reynolds numbers. Information regarding lift and pitching-moment characteristics, drag characteristics, and loading characteristics is provided.
Date: October 22, 1951
Creator: Graham, Robert R.
Object Type: Report
System: The UNT Digital Library
Aerodynamic Characteristics of Four Bodies of Revolution Showing Some Effects of Afterbody Shape and Fineness Ratio at Free-Stream Mach Numbers From 1.50 to 1.99 (open access)

Aerodynamic Characteristics of Four Bodies of Revolution Showing Some Effects of Afterbody Shape and Fineness Ratio at Free-Stream Mach Numbers From 1.50 to 1.99

The effects of fineness ratio (14.2 and 12.2) and boattailing on aerodynamic characteristics of four bodies of revolution at Mach numbers from 1.50 to 1.99 within a range of angles of attack from 0 degrees 10 degrees at an approximate Reynolds number of 35x10(superscript)6 based on body length were investigated. A comparison of experimental data with available theory is included. At zero angle of attack, fineness ratio has no appreciable effect on model characteristics while boattailing and boattail convergence significantly affect fore drag and base drag.
Date: May 22, 1951
Creator: Cohen, Robert J.
Object Type: Report
System: The UNT Digital Library
The torsional deflections of several propellers under operating conditions (open access)

The torsional deflections of several propellers under operating conditions

Report presenting propeller-blade torsional-deflection data obtained during an investigation of the pressure distribution on constant-chord solid aluminum-alloy blades differing only in camber and thickness. Testing indicated that thinner blades were able to produce greater amounts of deflection. Results regarding torsional deflections are also provided.
Date: June 22, 1951
Creator: Gray, W. H. & Allis, A. E.
Object Type: Report
System: The UNT Digital Library
Performance characteristics of aircraft cooling ejectors having short cylindrical shrouds (open access)

Performance characteristics of aircraft cooling ejectors having short cylindrical shrouds

The factors affecting the performance of ejector suitable for aircraft cooling are investigated theoretically and experimentally. The investigation covers a range of shroud-to-nozzle diameter ratios from 1.1 to 1.6, of shroud lengths from 0.2 to 2.28 nozzle diameters, of secondary-to-primary weight-flow ratios from 0 to 0.12, and of ambient-to-nozzle pressure ratios from 0.7 to 0.06. The results of a simplified theoretical analysis based on each type of flow are in good agreement with those experimentally obtained.
Date: May 22, 1951
Creator: Kochendorfer, Fred D. & Rousso, Morris D.
Object Type: Report
System: The UNT Digital Library
Flight investigation of the effect of control centering springs on the apparent spiral stability of a personal-owner airplane (open access)

Flight investigation of the effect of control centering springs on the apparent spiral stability of a personal-owner airplane

Report presents the results of a flight investigation conducted on a typical high-wing personal-owner airplane to determine the effect of control centering springs on apparent spiral stability. Apparent spiral stability is the term used to describe the spiraling tendencies of an airplane in uncontrolled flight as affected both by the true spiral stability of the perfectly trimmed airplane and by out-of-trim control settings. Centering springs were used in both the aileron and rudder control systems to provide both a positive centering action and a means of trimming the airplane.
Date: March 22, 1951
Creator: Campbell, John P.; Hunter, Paul A.; Hewes, Donald E. & Whitten, James B.
Object Type: Report
System: The UNT Digital Library
Corrosion Data for Type 347 Stainless Steel Pipe Waste Metal Recovery Process (open access)

Corrosion Data for Type 347 Stainless Steel Pipe Waste Metal Recovery Process

Introduction: "A limited test progress for the evaluation of type 347 stainless steel pipe which failed the Huey (?) test has been complicated. The tests reported herein were similar in scope to those reported in document number EW-20765, Corrosion Tests on Stainless Steel Plate, Waste Metal Recovery Process. Material tested was obtained on order number EWC-8553, National Tube Company Heat #3X9741. Lots 9789 and 9790."
Date: May 22, 1951
Creator: Sanborn, Kenneth L.
Object Type: Report
System: The UNT Digital Library
Health-Physics Monthly Information Report. July 1951 (open access)

Health-Physics Monthly Information Report. July 1951

None
Date: August 22, 1951
Creator: Bradley, J. E. & Burbage, J. J.
Object Type: Report
System: The UNT Digital Library
Increased process water pressure to 105 buildings (open access)

Increased process water pressure to 105 buildings

This document discusses increases in water pressure from the 190 Building process pumps which has been contemplated for a range of pressures up to 550 PSIG. The existing process pumps are dual units, consisting of a steam turbine driven primary pump operated: in series with an electric driven secondary pump. The secondary pumps installed in 100-B, D, F, and H Areas were designed for 400 PSIG working pressure, and were given factory hydrostatic tests of 600 PSIG. The 100-DR pumps were given factory hydrostatic tests of 650 PSIG. The Ingersoll-Rand Company advises that a working pressure of 425 PSIG is as high as they would-recommend for pump casing pressure on the secondary pumps. In consideration of problems incident to increased operating pressures, the immediate limiting factor is the total head pressure permissible on secondary pump casings. Other limiting factors are filter plant capacities, and 183 process water capacities.
Date: February 22, 1951
Creator: Measly, H. F.
Object Type: Report
System: The UNT Digital Library
Fundamental Equations Describing Neutron Behavior in a Cavity (open access)

Fundamental Equations Describing Neutron Behavior in a Cavity

This report provides fundamental equations and maps to calculate neutron behavior in a spherical cavity.
Date: May 22, 1951
Creator: Willmer, D. B. & Imhoff, D. H.
Object Type: Report
System: The UNT Digital Library
Mercury Amalgam Bonding of Uranium and Copper (open access)

Mercury Amalgam Bonding of Uranium and Copper

Technical report summarizing one phase of work done to develop methods of bonding uranium to a metal which is a good conductor of heat. Silver was chosen for contact with uranium because it is easy to plate on uranium and there is no danger of brittle Ag-U compounds being formed at elevated temperatures. [From Abstract]
Date: January 22, 1951
Creator: Glasgow, L. G.
Object Type: Report
System: The UNT Digital Library
Preliminary Investigation of Helmholtz Resonators for Damping Pressure Fluctuations in 3.6-Inch Ram Jet at Mach Number 1.90 (open access)

Preliminary Investigation of Helmholtz Resonators for Damping Pressure Fluctuations in 3.6-Inch Ram Jet at Mach Number 1.90

Memorandum presenting an investigation conducted at Mach number 1.90 to determine if Helmholtz resonators can be used in a typical ramjet configuration to damp pressure pulsations associated with shock oscillations. Only one of the two resonators was found to effectively damp pressure pulsations that occurred when the ram jet was operating in the vicinity of its peak pressure recovery. Neither was found to effectively damp pressure pulsations over the entire range of ramjet operating conditions.
Date: May 22, 1951
Creator: Fox, Jerome L.
Object Type: Report
System: The UNT Digital Library