Technical Report Archive & Image Library (TRAIL) - 50 Matching Results

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Drag Minimization for Wings and Bodies in Supersonic Flow

Description: "The minimization of inviscid fluid drag is studied for aerodynamic shapes satisfying the conditions of linearized theory, and subject to imposed constraints on lift, pitching moment, base area, or volume. The problem is transformed to one of determining two-dimensional potential flows satisfying either Laplace's or Poisson's equations with boundary values fixed by the imposed conditions. A general method for determining integral relations between perturbation velocity components is developed. … more
Date: November 29, 1957
Creator: Heaslet, Max A. & Fuller, Franklyn B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Endurance Evaluation of Sintered, Porous, Strut-Supported Turbine Blades made by Federal-Mogul-Bower-Bearings, Incorporated, under Bureau of Aeronautics Contract NOas 55-124-C

Description: Four strut-supported, transpiration-cooled turbine blades were investigated experimentally in a turbojet engine. The blade shells were fabricated by the mold-sintering method with spherical stainless-steel powder. Two blades were investigated in order to evolve suitable capping methods for the blade tip. Two other blades were used to evaluate the durability of the porous-shell material. The blades were investigated at a turbine-tip speed of 1305 feet per second, an average turbine-inlet tempera… more
Date: November 26, 1957
Creator: Hickel, Robert O. & Richards, Hadley T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Solid State Division Annual Progress Report for Period Ending August 31, 1957

Description: Report issued by the Oak Ridge National Laboratory discussing annual progress made by the Solid State Division. Work and research progress made during 1957 is presented. This report includes tables, illustrations, and photographs.
Date: November 26, 1957
Creator: Billington, D. S. & Crawford, J. H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of vertical location of wing and horizontal tail on the aerodynamic characteristics in pitch at Mach numbers from 0.60 to 1.40 of an airplane configuration with an unswept wing

Description: Report presenting an experimental investigation to determine the effects of vertical location of an unswept wing and horizontal tail on the aerodynamic characteristics in pitch of a wing-body-tail combination. The wings had an aspect ratio of 3.09, a taper ratio of 0.39, the quarter-chord line swept back 11.5 degrees, and biconvex sections.
Date: November 20, 1957
Creator: Stivers, Louis S., Jr. & Lippmann, Garth W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental lift of low-aspect-ratio triangular wings at large angles of attack and supersonic speeds

Description: Report presenting testing of three wings of different aspect ratios at a range of angles of attack to provide information on the effects of large angles of attack on the lift and normal force on triangular wings in a specific Mach number range. Results regarding the comparisons with data from semispan tests, prediction of lift and normal force and comparison with the experiment, and maximum lift coefficient are provided.
Date: November 20, 1957
Creator: Hill, William A., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight data pertinent to buffeting and maximum normal-force coefficient of the Douglas X-3 research airplane

Description: Report presenting the X-3 airplane, which has a straight 4.5-percent-thick wing of modified hexagonal section, which has been flown to maximum wing normal-force coefficients in the Mach number range from 0.7 to 1.1 at an average altitude of 30,000 feet. Measurements were made of airplane and wing-panel maximum normal-force coefficients and of some buffeting characteristics.
Date: November 20, 1957
Creator: Baker, Thomas F.; Martin, James A. & Scott, Betty J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Transonic Wind-Tunnel Tests of the Launch, Jettison, and Longitudinal Characteristics of an Airplane and Missile Model Combination

Description: Report presenting tests of an airplane model equipped with missiles to investigate the capability of that combination to achieve satisfactory launching and jettisoning of the missiles. Information about pylon modifications, missiles in launch positions, missile trajectory, and missiles in jettison positions is provided.
Date: November 20, 1957
Creator: Cleary, Joseph W.; Frank, Joseph L. & Dewey, C. Forbes, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Organic Moderated Reactor Experiment Progress Report: August-October 1956

Description: Report describing technical progress on the design and construction of an Organic Moderated Reactor Experiment (OMRE), to be operated at the National Reactor Testing Station in Arco, Idaho. "This is the second report of the series, and covers the period from August 1, 1956 through October 31, 1956" (p. 3).
Date: November 15, 1957
Creator: Trilling, C. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Plating Thickness Tester

Description: An electromagnetic eddy current instrument is described that is capable of measuring copper and nickel plating 1 to 8 mils thick plated on bismuth mandrils of various sizes and shapes.
Date: November 15, 1957
Creator: Fitch, C. E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Reactor Physics Primer

Description: Report that describes the reactor physics of the processes used to produce plutonium at Hanford Laboratories. This includes a basic explanation of nuclear physics and the principles of the reactor process.
Date: November 15, 1957
Creator: Lockwood, E. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of the Low-Speed Flight Characteristics of a 1/15-Scale Model of the Convair XB-58 Airplane

Description: Report presenting an investigation of the low-speed stability and control characteristics of a 1/15-scale free-flying model of the Convair XB-58 airplane. Results regarding the longitudinal stability and control and a pod-drop investigation are provided.
Date: November 14, 1957
Creator: Paulson, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of the Low-Speed Flight Characteristics of a 1/15-Scale Model of the Convair XB-58 Airplane: Coord. No. AF-AM-15

Description: Memorandum presenting an investigation of the low-speed stability and control characteristics of a scale free-flying model of the Convair XB-58 airplane. The model was flown over an angle-of-attack range from 9 to 30 degrees and only relatively low-altitude conditions were simulated. The stability and control characteristics were found to be satisfactory over the range investigated with the center of gravity at the 0.25 mean aerodynamic chord.
Date: November 14, 1957
Creator: Paulson, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Free-Stream Reynolds Number, Engine Installation, and Model Scale on Stability Characteristics of a Translating-Spike Inlet at Mach 2.0

Description: Memorandum presenting the effect of free-stream Reynolds number, engine installation, and model scale on inlet stability limits and on the amplitude and frequency of buzz. The data were taken at a free-stream Mach number of 2.0 and angles of attack from 0 to 6 degrees. Results regarding free-stream Reynolds number effect, model scale, and effect of engine on stability are provided.
Date: November 13, 1957
Creator: Musial, Norman T. & Bowditch, David
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of free-stream Reynolds number, engine installation, and model scale on stability characteristics of a translating-spike inlet at Mach 2.0

Description: Report presenting the effect of free-stream Reynolds number, engine installation, and model scale on inlet stability limits and on the amplitude and frequency of buzz. The data was obtained at mach number 2.0 and a range of angles of attack. Results regarding the free-stream Reynolds number effect, model scale, and effect of engine on stability are provided.
Date: November 13, 1957
Creator: Musial, Norman T. & Bowditch, David
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor-tip speed 8: Internal flow conditions of a two-stage turbine with a downstream stator

Description: Report presenting an investigation of a two-stage turbine with a downstream stator to determine the interstage flow conditions of the turbine. Results regarding stage efficiency and work output, first-stage performance, second-stage performance, and downstream-stator performance are provided.
Date: November 13, 1957
Creator: Petrash, Donald A.; Davison, Elmer H. & Schum, Harold J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Thermal Stability of a Commercial Propyl Pentaborane (HEF-2) in the Range 147 Degree to 190 Degree C

Description: Memorandum presenting an investigation of the thermal stability of a commercial grade of propyl pentaborane at temperatures of 147 and 190 degrees Celsius. The products of decomposition are hydrogen, hydrocarbons, and a solid nonvolatile yellow boron hydride.
Date: November 13, 1957
Creator: McDonald, G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Thermal Stability of a Commercial Propyl Pentaborane (HEF-2) in the Range 147 to 190 Degrees C

Description: Memorandum presenting an investigation of the thermal stability of a commercial grade of propyl pentaborane (HEF-2) at temperatures of 147 and 190 degrees Celsius. The products of decomposition are hydrogen, hydrocarbons, and a solid nonvolatile yellow boron hydride. An equation is provided that can be used to calculate the approximate time required to decompose 20 percent of propyl pentaborane at other temperatures.
Date: November 13, 1957
Creator: McDonald, G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Zircex Kinetics And Uranium Loss Study

Description: "A study was made of the effects of temperature, impurities in the hydrogen chloride, flow rates, and niobium content on both the reaction rates and insoluble uranium losses in the Zircex Process is presented."
Date: November 13, 1957
Creator: Carter, Jr, T. J. & Stone, R. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Surge-Inception Study in a Two-Spool Turbojet Engine, Revised

Description: "A two-spool turbojet engine was operated in the Lewis altitude wind tunnel to study the inception of compressor surge. In addition to the usual steady-state pressure and temperature measurements, the compressors were extensively instrumented with fast-response interstage pressure transducers. Thus it was possible to obtain maps for both compressors, pressure oscillations during rotating stall, effects of stall on efficiency, and stage-loading curves" (p. 1).
Date: November 12, 1957
Creator: Wallner, Lewis E.; Lubick, Robert J. & Saari, Martin J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Results of the Flight Test of a 0.13-Scale Rocket-Boosted Model of the McDonnell F4H-1 Airplane Between Mach Numbers of 0.20 and 1.90

Description: Report discussing tests performed with a rocket-boosted model of the McDonnell F4H-1 airplane at transonic and supersonic speeds. Special attention is given to the external drag coefficient at various Mach numbers. Large pitching oscillations were also noted at Mach numbers between 0.20 and 1.17, which made it impossible to determine the drag at that range.
Date: November 8, 1957
Creator: Hastings, Earl C., Jr. & Dickens, Waldo L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Results of the flight test of a 0.13-scale rocket-boosted model of the McDonnell F4H-1 airplane between Mach numbers of 0.20 and 1.90: TED No. NACA AD 3115

Description: From Summary: "A flight test was conducted with a 0.13-scale rocket-boosted model of the McDonnell F4H-1 airplane configuration at transonic and supersonic speeds. The external drag coefficient varied from a value of 0.044 at a Mach number of 1.17 to 0.045 at a Mach number of 1.40 and then decreased to 0.041 at a Mach number of 1.90. The limited oscillatory data available indicate the existence of a coupled longitudinal-lateral motion in the Mach number range from 0.20 to 1.17."
Date: November 8, 1957
Creator: Hastings, Earl C., Jr. & Dickens, Waldo L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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