Technical Report Archive and Image Library (TRAIL) - 272 Matching Results

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Abnormal grain growth in M-252 and S-816 alloys

Description: Report discussing an experimental investigation was carried out on air- and vacuum-melted M-252 and S-816 alloys to find conditions of heating and hot-working which resulted in abnormal grain growth. The experiments were mainly limited to normal conditions of heating for hot-working and heat treatment and normal temperatures of solution treatment were used to allow grain growth after susceptibility to abnormal grain growth was developed by various experimental conditions. Results indicated that small reductions of essentially strain-free metal were the basic cause of such grain growth.
Date: November 1957
Creator: Decker, R F; Rush, A I; Dano, A G & Freeman, J W
Partner: UNT Libraries Government Documents Department

Abnormal grain growth in nickel-base heat-resistant alloys

Description: From Introduction: "The data included in this report for Nimonic 80A alloy, for instance, represent experiments carried out to help clarify a production problem of grain-size control in an alloy which has been extensively used. The general procedure of the investigation was to carry out controlled laboratory experiments on samples of bar stock to find conditions of heating and hot-working which resulted in abnormal grain growth."
Date: December 1957
Creator: Decker, R F; Rush, A I; Dano, A G & Freeman, A G
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of a circular cylinder at Mach number 6.86 and angles of attack up to 90 degrees

Description: Pressure-distribution and force tests of a circular cylinder have been made in the Langley 11-inch hypersonic tunnel at a Mach number of 6.88, a Reynolds number of 129,000, and angles of attack up to 90 degrees. The results are compared with the hypersonic approximation of Grimminger, Williams, and Young and a simple modification of the Newtonian flow theory. An evaluation of the crossflow theory is made through comparison of present results with available crossflow Mach number drag coefficients.
Date: January 1957
Creator: Penland, Jim A
Partner: UNT Libraries Government Documents Department

Aerodynamic interference of slender wing-tail combinations

Description: From Introduction: "In the present paper, the emphasis is placed on calculating the variations of total forces and moments with angles of attack and sideslip for a number of slender plane and cruciform wing-tail combinations and for some airplane-type arrangements of a plane wing and a horizontal and vertical tail."
Date: January 1957
Creator: Sacks, Alvin H
Partner: UNT Libraries Government Documents Department

Analysis of horizontal-tail loads in pitching maneuvers on a flexible swept-wing jet bomber

Description: From Introduction: "The analysis of flight data in the present report is, to a large extent, based on analyses and information contained in references 1 and 2 for wing deflections, reference 3 for horizontal-tail parameters, reference 4 for airplane lift-curve slopes and angles of zero lift, and reference 5 for wing centers of pressure."
Date: December 1957
Creator: Aiken, William S , Jr
Partner: UNT Libraries Government Documents Department

Analysis of operational airline data to show the effects of airborne weather radar on the gust loads and operating practices of twin-engine short-haul transport airplanes

Description: From Introduction: "The data for operations both with and without radar installed have been analyzed and the results are presented in this paper. Although these results are of limited extent, they provide a basis for early examination of any trends in the gust loads and associated operating practices which might be attributed to the use of radar."
Date: November 1957
Creator: Copp, Martin R & Walker, Walter G
Partner: UNT Libraries Government Documents Department

An analysis of the effect of several parameters on the stability of an air-lubricated hydrostatic thrust bearing

Description: From Introduction: "The present investigation considers a simple nonrotating thrust bearing consisting of two round flat disks of finite diameter separated by a thin film of air. The nonlinear differential equations governing the motion of the bearing when disturbed were solved on a high-speed digital computing machine. In addition, these solutions provide a means for checking the validity of more simplified solutions (e.g., ref. 1)."
Date: October 1957
Creator: Roudebush, William H
Partner: UNT Libraries Government Documents Department

Analytical investigation of the effect of water injection on supersonic turbojet-engine - inlet matching and thrust augmentation

Description: From Introduction: "In order to provide engine-inlet matching to prevent such mass flow spillage and the attendant drags, much mechanical complication has been introduced. References 1 and 2 propose employing this principle at subsonic and supersonic speeds to achieve thrust augmentation. The merits of the system for supersonic engine-inlet airflow matching, as well as thrust augmentation, appear considerable; and a comparative study with existing fixed- and variable-geometry inlets was therefore undertaken."
Date: January 1957
Creator: Beke, Andrew
Partner: UNT Libraries Government Documents Department

Base pressure at supersonic speeds on two-dimensional airfoils and on bodies of revolution with and without fins having turbulent boundary layers

Description: An analysis has been made of available experimental data to show the effects of most of the variables that are more predominant in determining base pressure at supersonic speeds. The analysis covers base pressures for two-dimensional airfoils and for bodies of revolution with and without stabilizing fins and is restricted to turbulent boundary layers. The present status of available experimental information is summarized as are the existing methods for predicting base pressure. A simple semiempirical method is presented for estimating base pressure. For two-dimensional bases, this method stems from an analogy established between the base-pressure phenomena and the peak pressure rise associated with the separation of the boundary layer. An analysis made for axially symmetric flow indicates that the base pressure for bodies of revolution is subject to the same analogy. Based upon the methods presented, estimations are made of such effects as Mach number, angle of attack, boattailing, fineness ratio, and fins. These estimations give fair predictions of experimental results. (author).
Date: January 1, 1957
Creator: LOVE EUGENE S
Partner: UNT Libraries Government Documents Department