Technical Report Archive & Image Library (TRAIL) - 132 Matching Results

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Additional Fatigue Tests on Effects of Design Details in 355-T6 Sand-Cast Aluminum Alloy

Description: From Introduction: "Reported herein are results of the additional direct-stress fatigue tests on: (1) a plate-type specimen with cored centrally located hole and (2) 0.300-inch-diameter round polished specimens with various degrees of porosity."
Date: March 10, 1954
Creator: Eaton, I. D. & Youra, John A.
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics at transonic and supersonic speeds of a rocket-propelled airplane configuration having a 52.5 degree delta wing and a low, swept horizontal tail

Description: Report presenting a flight investigation over a range of Mach numbers to determine the aerodynamic characteristics at low lift of a rocket model of an airplane with a 52.5 degree delta wing of aspect ratio 3.08 and NACA 65A003 airfoil sections in the streamwise direction and a low, swept horizontal tail. Results regarding the longitudinal trim, lift, drag, longitudinal static stability, damping in pitch, and directional static stability are provided.
Date: March 29, 1954
Creator: Kehlet, Alan B.
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics including effects of wing fixes of a 1/20-scale model of the Convair F-102 airplane at transonic speeds

Description: From Introduction: "Results from the tests in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01 are presented in reference 1. Reported herein are results obtained from the tests in the Langley 8-foot transonic tunnel of the model with no control deflections at Mach numbers 0.6 to 1.12 for angles of attack up to 34^o
Date: March 18, 1954
Creator: Osborne, Robert S. & Wornom, Dewey E.
Partner: UNT Libraries Government Documents Department
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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 6.86, a Reynolds number of 129,000 based on diameter, and angles of attack up to 90 degrees. The results are compared with the hypersonic approximation of Grimminger, Williams, and Young and with a simple modification of the Newtonian flow theory. The comparison of experimental results shows that either theory gives adequate general aerodynamic characteristic… more
Date: March 11, 1954
Creator: Penland, Jim A.
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics of a full-span trailing-edge control on a 60 degree delta wing with and without a spoiler at Mach number 1.61

Description: Report presenting an investigation at Mach number 1.61. to determine the aerodynamic characteristics of a full-span trailing-edge control on a 60 degree delta wing with and without a partial-span spoiler mounted on the wing just ahead of the control. Pressure distribution and hinge-moment measurements were made over a range of angles of attack and control deflection. Results indicated that regions of increase pressure due to flow separation ahead of the control at the larger control deflections… more
Date: March 10, 1954
Creator: Lord, Douglas R. & Czarnecki, K. R.
Partner: UNT Libraries Government Documents Department
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Aerodynamics of slender wings and wing-body combinations having swept trailing edges

Description: From Introduction: "In the present paper, a general method is developed for solving low-aspect-ratio problems involving shed vortex sheets. Both direct and inverse problems are considered. The method is applicable for all planar problems where the velocity boundary conditions can be made homogeneous by differentiation in either the streamwise or the spanwise directions."
Date: March 1954
Creator: Mirels, Harold
Partner: UNT Libraries Government Documents Department
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An air-flow-direction pickup suitable for telemetering use on pilotless aircraft

Description: From Summary: Test results are presented which indicate that the pickup is aerodynamically stable and has accuracy, obtained from a bench calibration, of better than 0.3^o under conditions including acceleration up to 20g in any direction, Mach numbers from 0.5 to 2.8, and dynamic pressures up to at least 65 psi. Equations and curves which can be used to obtain flow direction at the center of gravity of a maneuvering model are presented."
Date: March 10, 1954
Creator: Ikard, Wallace L.
Partner: UNT Libraries Government Documents Department
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Altitude performance and operational characteristics of an XT38-A-2 turboprop engine

Description: From Introduction: "Reported herein are the over-all engine performance and the starting and windmilling characteristics. Data are presented in the form of performance maps at each flight condition to show the effects of altitude and flight Mach number on various engine-performance variables. The effect of engine deterioration with operating time on performance is also discussed."
Date: March 12, 1954
Creator: Essig, R. H. & Schulze, F. W.
Partner: UNT Libraries Government Documents Department
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Altitude performance of compressor, turbine, and combustor components of 600-B9 turbojet engine

Description: From Introduction: "The purpose of this report is (1) to describe the performance of each component over a range of altitudes, (2) to show the effect of flight conditions on operating point of each component, and (3) to summarize briefly the effects of changes in component performance with flight condition on the over-all engine performance."
Date: March 15, 1954
Creator: Prince, William R. & Wile, Dorwin B.
Partner: UNT Libraries Government Documents Department
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An analytical and experimental study of the transient response of a pressure-regulating relief valve in a hydraulic circuit

Description: From Introduction: "This report presents an analysis of the response of the relief valve to sudden flow-demand changes. The analysis can be applied to the design of relief valves to satisfy given response specifications and to predict the stability of the valve in a specific hydraulic circuit. For this reason, derivatives of all the constants employed are included in the report."
Date: March 1954
Creator: Gold, Harold & Otto, Edward W.
Partner: UNT Libraries Government Documents Department
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An Automatic Micromuffle for the Determination of Ash in Carbonaceous Material

Description: Abstract: An automatic micromuffle for the determination of the ash content of small samples of carbonaceous material is comprised of a furnace of the radiant-heating type with a direct reading pyrometer for temperature control. This furnace can be assembled with a minimum of labor using parts available from scientific laboratory apparatus companies.
Date: March 1954
Creator: Meyrowitz, Robert & Massoni, C. J.
Partner: UNT Libraries Government Documents Department
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Chordwise pressures and section moment force and moment coefficients at high subsonic speeds near midspan of a tapered 35 degree sweptback wing with a flap-type control and an attached tab

Description: Report presenting an investigation in the high-speed tunnel to determine the effects on the chordwise pressure and section force and moment coefficients near midspan of deflecting a flap-type control with an attached tab on a swept wing. The semispan 35 degree sweptback wing had an NACA 65A006 airfoil section, an aspect ratio of 4, and a taper ratio of 0.6.
Date: March 29, 1954
Creator: Hammond, Alexander D. & Keffer, Barbara M.
Partner: UNT Libraries Government Documents Department
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Combustion performance of two experimental turbojet annular combustors at conditions simulating high-altitude supersonic flight

Description: Report presenting an investigation of the performance of two experimental annular turbojet combustors at operating conditions typical of high-altitude supersonic flight. Results regarding combustion efficiency, combustor-outlet temperature profile, combustor pressure losses, and carbon and durability are provided.
Date: March 26, 1954
Creator: Zettle, Eugene V.; Norgren, Carl T. & Mark, Herman
Partner: UNT Libraries Government Documents Department
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Cooling requirements for stability of laminar boundary layer with small pressure gradient at supersonic speeds

Description: Report presenting the amount of cooling required to stabilize the two-dimensional supersonic laminar boundary layer for all Reynolds numbers for flows with pressure gradients of a magnitude usually encountered over slender aerodynamic shapes. It is determined that small pressure gradients have an appreciable effect on stability.
Date: March 1954
Creator: Low, George M.
Partner: UNT Libraries Government Documents Department
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A Design Study of Leading-Edge Inlets for Unswept Wings

Description: Note presenting a practical method, employing a lofting technique, for determining the profile coordinates of an air inlet for the leading edge of an airfoil from formulas which are dependent only on the airfoil coordinates and on the height of the opening. It was found that the base-profile concept of thin-airfoil theory could be applied to a ducted airfoil with satisfactory results. Results regarding design inlets, modified inlets, and end-closure shape are provided.
Date: March 1954
Creator: Dannenberg, Robert E.
Partner: UNT Libraries Government Documents Department
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Determination of Tritium in Urine and Water

Description: The sample, water or urine, is prepared for counting in a vacuum line. Urine or water is dropped onto metallic calcium, and hydrogen and tritium are evolved. The gas flowing into the evacuated system is passed through liquid nitrogen cooled traps to remove unreacted water and condensable gases. The gas is allowed to flow into a tube similar to a Geiger-Muller tube until a pressure of 15 cm of mercury is attained. Ethylene and argon are added to give a total pressure of 22 cm of mercury. The bet… more
Date: March 1954
Creator: McClelland, Jean.; Milligan, Morris F.; Bayhurst, Barbara P.; Eutsler, Bernard C.; Foreman, W. W.; Head, Billye M. et al.
Partner: UNT Libraries Government Documents Department
open access

Diffraction Studies of Possible Ordering in α-brass

Description: Recently, there has been some evidence to point to possible ordering in the α-brasses. Masumoto et al. have concluded from their specific heat measurements that there is a possibility of ordering in the α-brasses. In particular they observed an anomaly in the specific heat curves for the α-brasses for the temperature range from 200 to 260°C and explained these results upon the basis of a change in local or short range order in α-brasses at these temperatures. In connection with the study of rad… more
Date: March 29, 1954
Creator: Keating, David, T.
Partner: UNT Libraries Government Documents Department
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Drag and longitudinal trim characteristics of a low-tail version of the North American YF-100A airplane as determined from the flight test at low lift of a 0.11-scale rocket-powered model at Mach numbers between 0.75 and 1.78

Description: Report presenting drag and longitudinal trim characteristics at low lift of a low-tail version of the North American YF-100A airplane as obtained from the flight test of a 0.11-scale rocket model at a range of Mach numbers. Longitudinal stability data and some qualitative damping-in-pitch data are also provided.
Date: March 29, 1954
Creator: Blanchard, Willard S., Jr.
Partner: UNT Libraries Government Documents Department
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Dynamic corrosion of nickel at 1500 F by sodium hydroxide with various additives in a torrid circulating apparatus

Description: Metallic sodium chloride, calcium hydride, sodium aluminate, and an alloy of aluminum were added to sodium hydroxide in individual nickel tubes and corrosion tested at a fluid velocity of 15 feet per second with a hot-section temperature of 1500 degrees F and a hot-to-cold-section temperature difference of 20 degrees to 30 degrees F. A toroid circulating apparatus was used and the specimens were run for a period of 24 hours or until failure occurred. Various methods of evaluating the severity o… more
Date: March 1954
Creator: Desmon, Leland G. & Mosher, Don R.
Partner: UNT Libraries Government Documents Department
open access

The Effect of Dynamic Loading on the Strength of an Inelastic Column

Description: From Summary: "The maximum loads of idealized inelastic H-section columns whose pinned ends approach each other at a constant rate are presented. The solutions indicate that as the rate of end displacement becomes smaller, the dynamic buckling solutions approach the static solution as a lower limit. The effects of inertia forces are apparently negligible at rates of end displacement comparable to those normally used in static column tests."
Date: March 1954
Creator: Brooks, William A., Jr. & Wilder, Thomas W., III
Partner: UNT Libraries Government Documents Department
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Effect of heat treatment upon the microstructure and hardness of a wrought cobalt-base alloy stellite 21 (AMS 5385)

Description: Report presenting an investigation of the response of wrought Stellite 21, a typical cobalt-base alloy, to heat treatment. The alloy was solution-treated and transformed by aging and isothermal transformation at temperatures of 1200 to 1950 degrees Fahrenheit for periods of 5 minutes to 72 hours. Results regarding the solution-treated structure, precipitation by isothermal transformation, precipitation by aging, grain boundary behavior, and hardness are provided.
Date: March 1954
Creator: Clauss, F. J. & Weeton, J. W.
Partner: UNT Libraries Government Documents Department
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