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The Corrosion of Miniature Fuel Plates in Simulated Reactor Cooling Water

Description: Technical report issued as one of a series of reports concerned with corrosion studies for the Materials Resting Reactor, created to both determine the effect of various practices for fuel plate fabrication on corrosion resistance and to determine the extent of penetration of the fuel plates by localized corrosion attack. [From Introduction]
Date: December 18, 1950
Creator: English, James L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Engineers 100 Areas technical activities report July 1950

Description: Progress is reported by the Mechanical Development group and by the Plant Assistance group. The Mechanical Development group reports on the thimble removal program, special pile measurements and instruments, graphite sampling, and the ruptured slug problem. The Plant Assistance group reports on technical information on the B, D, F, and H piles, special request container slug, exposure of P-10 fuel slugs, slug corrosion studies, front tube corrosion, and flow laboratory experiments.
Date: August 18, 1950
Creator: Lewis, W. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Hanford Works Monthly Report: August 1950

Description: This is a progress report of the production reactors on the Hanford Reservation for the month of August 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: September 18, 1950
Creator: Prout, G. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Hanford Works monthly report, July 1950

Description: This is a progress report of the production reactors on the Hanford Reservation for the month of July 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: August 18, 1950
Creator: Prout, G. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lateral-control investigation of flap-type and spoiler-type controls on a wing with quarter-chord-line sweepback of 60 degrees, aspect ratio 2, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bump method

Description: Report presenting an investigation by the transonic-bump method through a range of Mach numbers in the high speed 7- by 10-foot tunnel to determine the lateral-control characteristics of a semispan wing-fuselage combination equipped with flap-type and spoiler-type controls. Both the flap-type and spoiler-type controls provide lateral control through the Mach number range investigated.
Date: July 18, 1950
Creator: Hammond, Alexander D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The transonic characteristics of a low-aspect-ratio triangular wing with a constant-chord flap as determined by wing-flow tests, including correlation with large-scale tests

Description: Report presenting wing-flow-method measurements for 0.47 to 1.15 Mach number of the longitudinal-stability and -control characteristics of a triangular wing of aspect ratio 2 equipped with a constant-chord flap. Changes in the lift-curve slope and aerodynamic-center position through the transonic speed range were moderate and gradual. Results regarding triangular-wing characteristics, flap characteristics, and a comparison of the wind-tunnel and free-flight-test results at higher Reynolds numbe… more
Date: August 18, 1950
Creator: Rathert, George A., Jr.; Rolls, L. Stewart & Hanson, Carl M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure Distributions on the Blade Sections of the NACA 10-(5)(066)-03 Propeller Under Operating Conditions

Description: A report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for eight radial stations of the NACA 10-(5)(066)-03 propeller.
Date: April 18, 1950
Creator: Evans, Albert J. & Luchuk, Wallace
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure Distributions on the Blade Sections of the NACA 10-(0)(066)-03 Propeller Under Operating Conditions

Description: The fifth report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for nine radial stations of the NACA 10-(0)(066)-03 propeller.
Date: May 18, 1950
Creator: Steinberg, Seymour & Milling, Robert W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of effect of span and spanwise location of plain and stepped spoiler ailerons on lateral control characteristics of a wing with leading edge swept back 51.3 degrees

Description: Report presenting a wind-tunnel investigation at low speed to determine the lateral control characteristics of a 51.3 degree sweptback-wing model equipped with either plain or stepped spoiler ailerons with a fixed projection of 5-percent-wing chord and various spans and spanwise locations. The results indicated that spanwise rolling-effectiveness charts of flap-type ailerons can not be used to predict effectiveness of spoiler-type ailerons on swept wings. Results regarding the wing aerodynamic … more
Date: January 18, 1950
Creator: Fischel, Jack & Hammond, Alexander D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Ditching Tests With a 1/16-Size Model of the Navy XP2V-1 Airplane at the Langley Tank No. 2 Monorail

Description: Report discussing tests using a model of the Navy XP2V-1 to study its performance when ditched. From Summary: "Various landing attitudes, speeds, and conditions of damage were simulated. The performance of the model was determined and recorded from visual observations, by recording time histories of the longitudinal decelerations, and by taking motion pictures of the ditchings."
Date: May 18, 1950
Creator: Fisher, Lloyd J. & Tarshis, Robert P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analytical investigation of flow and heat transfer in coolant passages of free-convection liquid-cooled turbines

Description: From Introduction: "An analytical investigation of the problems arising in connection with this cooling method was conducted at the NACA Lewis laboratory and is presented herein. This analysis investigates: (1) the smallest diameter hole that can be made without endangering the circulation of the liquid, and (2) methods of improving the circulation in a small-diameter hole."
Date: July 18, 1950
Creator: Eckert, E. R. G. & Jackson, Thomas W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tabulated Pressure Coefficients and Aerodynamic Characteristics Measured on the Wing of the Bell X-1 Airplane in Level Flight at Mach Numbers From 0.79 to 1.00 and in a Pull-Up at a Mach Number of 0.96

Description: "Tabulated pressure coefficients and aerodynamic characteristics are presented for six spanwise stations on the left wing of the Bell X-1 research airplane. The data were obtained in level flight at Mach numbers from 0.79 to 1.00 and in a pull-up to an airplane normal-force coefficient of 0.91 at a Mach number of approximately 0.96" (p. 1).
Date: September 18, 1950
Creator: Carner, H. Arthur & Payne, Mary M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Investigation at Mach Numbers From 0.8 to 1.4 to Determine the Zero-Lift Drag of Wings With 'M' and 'W' Plan Forms

Description: Report presenting testing of the zero-lift drag of two wings, one with 45 degree sweepforward of the inboard panel and 45 degree sweepback of the outboard panel ("M" wing) and the other with a reverse sweep ("W" wing) at a range of Mach numbers. Both wings were found to have greater drag than a sweptback wing and less drag than a rectangular wing at transonic speeds. The differences were reduced at Mach numbers above 1.25.
Date: September 18, 1950
Creator: Katz, Ellis; Marley, Edward T. & Pepper, William B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

NACA research on combustors for aircraft gas turbines 1: effects of operating variables on steady-state performance

Description: Some of the systematic research conducted by the NACA on aircraft gas-turbine combustors is reviewed. Trends depicting the effect of inlet-air pressure, temperature, and velocity and fuel-air ratio on performance characteristics, such as combustion efficiency, maximum temperature rise attainable, pressure loss, and combustor-outlet temperature distribution are described for a variety of turbojet combustors of the liquid-fuel type. These trends are further discussed as effects significant to the… more
Date: October 18, 1950
Creator: Olson, Walter T. & Childs, J. Howard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Stability and control characteristics of a 1/4-scale Bell X-5 airplane model in the landing configuration

Description: Report presenting an investigation of the static stability and control characteristics of a scale model of a preliminary Bell X-5 airplane design in the landing configuration with and without dive brakes. Results regarding the effects of slats, flaps, landing gear, gear doors, dive brakes and gap at the wing root are provided.
Date: December 18, 1950
Creator: Becht, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation at Mach numbers of 2.0 and 2.9 of several configurations of a supersonic ram-jet test vehicle

Description: Report presenting wind-tunnel tests at Mach numbers of 2.0 and 2.9 to investigate the aerodynamic characteristics of several configurations of a supersonic ram-jet test vehicle. Three low-aspect-ratio wing configurations, with the ram-jet engine located forward and below the wing, were tested in pitch at Mach number 2.0.
Date: August 18, 1950
Creator: Spahr, J. Richard & Robinson, Robert A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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