UNT Libraries Government Documents Department - 17 Matching Results

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Maching Techniques and Prodicers for Uranium, Graphite, Titanium, Zirconium, Thorium, Tantalum, Beryllium, Bismuth, Lithium, and Stellite

Description: Techniqnes are presented which are applicable in machining materinls such as U, graphite, Ti, Zr, Th, Ta, Be, Bi, Li, and stellite. Included in the general considerations are factors related to machinability of the materials, operating condition of the machines, and the condition of the cutting tools. In addition, industrial hygtene and safety aspects are examined. The techniques for each material are discussed in detail, the greatest attention being focused on uranium.
Date: November 4, 1952
Creator: Davis, Calvin
Item Type: Refine your search to only Report
open access

Flight Test Results of Rocket-Propelled Buffet-Research Models Having 45 Degree Sweptback Wings and 45 Degree Sweptback Tails Located in the Wing Chord Plane

Description: "Three rocket-propelled buffet-research models have been flight tested to determine the buffeting characteristics of a swept-wing- airplane configuration with the horizontal tail operating near the wing wake. The models consisted of parabolic bodies having 45 deg sweptback wings of aspect ratio 3.56, at aspect ratio of 0.3, NACA 64A007 airfoil sections, and tail surfaces of geometry and section identical to the wings. Two tests were conducted with the horizontal tail located in the wing chord p… more
Date: November 4, 1953
Creator: Mason, Homer P.
Item Type: Refine your search to only Report
open access

Some Effects of Leading-Edge Roughness on the Aileron Effectiveness and Drag of a Thin Rectangular Wing Employing a Full-Span Plain Aileron at Mach Numbers From 0.6 to 1.5

Description: Report presenting an investigation of the effects of adding leading-edge roughness to the surfaces of an unswept, untapered, 6-percent-thick, circular-arc-airfoil wing equipped with a full-span, 0.2-chord, plain, trailing-edge aileron. Results regarding the rolling-effectiveness data, addition of roughness on a wing, and variation of drag coefficient are provided.
Date: November 4, 1953
Creator: English, Roland D.
Item Type: Refine your search to only Report
open access

Wing loads on the Bell X-1 research airplane (10 percent thick wing) as determined by pressure-distribution measurements in flight at subsonic and transonic speeds

Description: Report presenting measurements of wing loads made on the left wing of the Bell X-1 research airplane. Data are presented within a wing-panel normal-force coefficient and Mach number range. Results regarding span load distributions, wing-panel aerodynamic characteristics, and wing-to-fuselage carry over are provided.
Date: November 4, 1953
Creator: Knapp, Ronald J. & Jordan, Gareth H.
Item Type: Refine your search to only Report
open access

Free-flight zero-lift drag-rise measurements of equivalent bodies of revolution of several versions of the Douglas XF4D-1 airplane at transonic speeds: TED No. NACA AD 394

Description: From Summary: "Free-flight tests have been conducted with small equivalent bodies of revolution representing different versions of the Douglas XF4D-1 airplane to determine the reduction in drag that would result from various modifications to the airplane. Results indicated that, at Mach numbers greater than 1, considerable reduction in drag would result from a thinner wing and tail, a reduction in wing-fillet thickness, and modified forward and rearward fuselage lines."
Date: November 4, 1954
Creator: Mitcham, Grady L.
Item Type: Refine your search to only Report
open access

Review of experimental investigations of liquid-metal heat transfer

Description: Experimental data of various investigators of liquid-metal heat-transfer characteristics were reevaluated using as consistent assumptions and methods as possible and then compared with each other and with theoretical results. The reevaluated data for both local fully developed and average Nusselt numbers in the turbulent flow region were found still to have considerable spread, with the bulk of the data being lower than predicted by existing analysis. An equation based on empirical grounds whic… more
Date: November 4, 1954
Creator: Lubarsky, Bernard & Kaufman, Samuel J.
Item Type: Refine your search to only Report
open access

Wind Tunnel Investigation at Low Speed of the Aerodynamic Characteristics of the Army Chemical Corps Model E112 Bomblets

Description: Report discussing an experimental investigation to determine the aerodynamic characteristics of the Army Chemical Corps model E112 bomblets. From Summary: "A detailed analysis has not been made; however, the results showed that a gap between model tips and the end plates or increasing the end-plate size for a solid model could result in a spirally stable configuration." A large amount of data collected from testing and photographs of the model are provided.
Date: November 4, 1955
Creator: Letko, William & Williams, James L.
Item Type: Refine your search to only Report
open access

Wind-tunnel investigation at low speed of the aerodynamic characteristics of the Army Chemical Corps model E112 bomblets

Description: "An experimental investigation has been made n the Langley stability tunnel to determine the aerodynamic characteristics of the Army Chemical Corps model E112 bomblets. A detailed analysis has not been made; however, the results showed that a gap between model tips and the end plates or increasing the end-plate size for a solid model could result in a spirally stable configuration" (p. 1).
Date: November 4, 1955
Creator: Letko, William & Williams, James L.
Item Type: Refine your search to only Report
open access

Definitive Scope of a Facility for E-Metal Product Segregation at the UO{sub 3} Plant Project CG-767

Description: E-Metal production is scheduled to start through the UO{sub 3} Plant in July of 1958. E-Metal is defined in HW-46138 as uranium metal enriched with U-235 to a level selected to be always-safe for non-metallic uranium forms, i.e. for compounds encountered during solvent extraction or calcination. Currently E-metal as selected contains 0.94% U-235 prior to irradiation. Planning of a segregation facility requires that the mixing of E-Metal with normal uranium be minimized, thereby preventing costl… more
Date: November 4, 1957
Creator: Gustafson, L. D.
Item Type: Refine your search to only Report
open access

A hydrogen peroxide turbojet-engine simulator for wing-tunnel powered-model investigations

Description: Report presenting a turbojet-engine-exhaust simulator utilizing a hydrogen peroxide gas generator developed for powered-model testing in wind tunnels with air exchange. The problems associated with jet exhaust simulation in a transonic wind tunnel which led to the selection of a liquid monopropellant are discussed. Static-data obtained with convergent nozzles are presented and shown to be in good agreement with ideal calculated values.
Date: November 4, 1957
Creator: Runckel, Jack F. & Swihart, John M.
Item Type: Refine your search to only Report
open access

Transonic Flutter Investigation of Arrowhead Wing With Tip Ailerons and Trailing-Edge Flaps

Description: Report presenting a transonic flutter investigation of models of a wing of a new fighter airplane with an arrowhead plan form, ailerons at the tips and flaps, and was cantilever mounted. Results regarding the run, point, panel behavior, scaling, and a comparison of the basic, modified, and locked ailerons are provided.
Date: November 4, 1957
Creator: Jones, George W., Jr. & Boswinkle, Robert W., Jr.
Item Type: Refine your search to only Report
open access

The use of a leading-edge area-suction flap and leading-edge modifications to improve the high-lift characteristics of an airplane model with a wing of 45 degree sweep and aspect ratio 2.8

Description: Report presenting an investigation on an airplane model with drooped horizontal tail and a highly tapered wing of aspect ratio 2.8 and 45 degrees of sweep. The primary purpose of the investigation was to determine what improvements in the control of leading-edge stall would be possible with the use of area suction on a leading-edge flap and with the leading-edge flap used with a modified or bulbous leading edge and chord extension.
Date: November 4, 1957
Creator: Koenig, David G. & Aoyagi, Kiyoshi
Item Type: Refine your search to only Report
open access

Use of Constant Diffuser Mach Number as a Control Parameter for Variable-Geometry Inlets at Mach Numbers of 1.8 to 2.0

Description: Memorandum presenting an analysis to determine the feasibility of using a constant diffuser Mach number to position a translating spike for optimum inlet performance. A control system incorporating this concept was investigated on a blunt lip, translating-spike inlet at flight Mach numbers of 1.8 to 2.0 and angles of attack up to 6 degrees. Results regarding inlet characteristics and performance with control are provided.
Date: November 4, 1957
Creator: Hearth, Donald P. & Anderson, Bernhard H.
Item Type: Refine your search to only Report
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