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Aerodynamic Characteristics of a 6-Percent-Thick Symmetrical Circular-Arc Airfoil Having a 30-Percent-Chord Trailing-Edge Flap at a Mach Number of 6.9

Description: Memorandum presenting an investigation of the flow characteristics over a 6-percent-thick symmetrical circular-arc airfoil section with a 30-percent-chord trailing-edge flap at a Mach number of 6.90 and a Reynolds number of 1.65 x 10(sub 6). The model was tested over an angle-of-attack range of 0 to 16 degrees and a flap-deflection range of -16 degrees to 16 degrees. Results regarding pressure results and aerodynamic characteristics are provided.
Date: June 5, 1956
Creator: Ridyard, Herbert W. & Fetterman, David E., Jr.
open access

Aircraft Nuclear Propulsion Project Quarterly Progress Report for Period Ending March 10, 1956

Description: This quarterly progress report of the Aircraft Nuclear Propulsion Project at ORNL records the technical progress of the research on circulating-fuel reactors and ether ANP research at the Laboratory under its Contract W-7405-eng-26. The report is divided into three major parts: I. Reactor Theory, Component Development, and Construction, II. Materials Research, and III. Shielding Research.
Date: June 13, 1956
Creator: Jordan, W. H.; Cromer, S. J. & Miller, A. J.
open access

Application of Scattering Theory to the Measurement of Turbulent Density Fluctuations by an Optical Method

Description: "An analysis shows that the scattering of unpolarized plane light waves which penetrate turbulent, transparent gases provides a measure of the average integral scale and intensity of the turbulent density fluctuations. The analysis is based upon the scattering coefficient deduced by Booker and Gordon and, thus, assumes isotropic fluctuations having an exponentially decaying (Markoffian) correlation function. Photometric data taken through turbulent boundary layers in air are found to conform fu… more
Date: June 1956
Creator: Stine, Howard A. & Winovich, Warren
open access

Attenuation of tangential-pressure oscillations in a liquid-oxygen - n-heptane rocket engine with longitudinal fins

Description: An investigation of the use of fins to prevent high-frequency combustion-pressure oscillations (screaming) in the combustion chamber of a 1000-pound-thrust rocket engine with a chamber pressure of 300 pounds per square inch and using liquid oxygen and n-heptane as propellants. Tangential combustion-pressure oscillations were found to be eliminated with longitudinal fins located in the combustion zone. Results regarding engine performance, effect of fins, and destructiveness of screaming are pro… more
Date: June 28, 1956
Creator: Priem, Richard J.
open access

A Bibliography of NACA Reports on Control of Turbojet Engines

Description: Memorandum presenting an annotated bibliography of NACA reports containing information of interest to designers and manufacturers of controls for turbojet engines. The eleven major topics include starting, acceleration, flame-out, temperature control, stability and dynamics of small disturbances, combustion dynamics, engine inlet diffuser control, steady-state engine performance, fuel systems, sensors, and general control system theory.
Date: June 28, 1956
Creator: Sanders, John C.
open access

Caps Clad with Aluminum-Silicon

Description: Approximately 15,000 "P" Process Aluminum caps clad with aluminum-silicon on the face and sides have been successfully canned. These caps were fabricated by the Aluminum Company of America from clad plate stock. An increase in canned slug yield of about two percent was realized from using these caps and no significant process problems indicated that the additional cost of clad plate might be off-set by the elimination of the centerless grinding now required on the side of the cap base. Therefor… more
Date: June 13, 1956
Creator: Farland, D. C.
open access

The change with mass-flow ratio of the cowl pressure drag of normal-shock inlets at supersonic speeds

Description: Report presenting pressure-drag coefficients and the changes in these coefficients with mass-flow ratio, which have been measured in tests of six open-nose conical cowls at an angle of attack of 0 degrees. Testing occurred in the Ames 8 by 8-inch supersonic wind tunnel at a range of Mach numbers. Results regarding pressure distributions, change in cowl pressure drag with mass-flow ratio, cowl pressure drag at a given mass-flow ratio, and changes in cowl pressure drag with mass-flow ratio as a f… more
Date: June 22, 1956
Creator: Davis, Wallace F. & Gowen, Forrest E.
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