Technical Report Archive & Image Library (TRAIL) - 31 Matching Results

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The Aeolotropic Elastic Relations for Uranium Crystals

Description: Handwritten report. This theoretical introduction to the anisotropic elastic properties of the orthorombic [sic] uranium crystal presents certain basic ideas which are useful in the study of experimental methods for determining preferred orientations in polycrystalline bodies. The method of analysis used to determine the elastic constants suggests explanations and correlations for the observations of sonic wave experiments on bars having preferred orientations and also serves as an introduction… more
Date: December 17, 1954
Creator: Merckx, K. R.
Partner: UNT Libraries Government Documents Department
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Altitude-wind-tunnel investigation of several afterburner configurations having moderately high burner-inlet velocities

Description: From Introduction: "The screech investigation, reported in reference 1, included a large number of afterburner configurations. Several of these configurations are presented herein to show the effects of afterburner-inlet gas whirl pattern, flame-holder design, and fuel distribution on performance as determined by combustion efficiency, augmented thrust ratio, and special fuel consumption."
Date: November 17, 1954
Creator: Schulze, F. W.; Bloomer, H. E. & Miller, R. R.
Partner: UNT Libraries Government Documents Department
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Analysis of Turbulent Heat Transfer, Mass Transfer, and Friction in Smooth Tubes at High Prandtl and Schmidt Numbers

Description: From Introduction: "In the analysis given herein, which was made at the NACA Lewis laboratory, the expression for eddy diffusivity given in reference 1 is modified in order to account for the effect of kinematic viscosity in reducing the turbulence in the region close to the wall. The effects of variable viscosity and of length-to-diameter ratio are also investigated."
Date: February 17, 1954
Creator: Deissler, Robert G.
Partner: UNT Libraries Government Documents Department
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Design and Evaluation of a Turbojet Exhaust Simulator, Utilizing a Solid-Propellant Rocket Motor, for Use in Free-Flight Aerodynamic Research Models

Description: A method has been developed for modifying a rocket motor so that its exhaust characteristics simulate those of a turbojet engine. The analysis necessary to the design is presented along with tests from which the designs are evaluated. Simulation was found to be best if the exhaust characteristics to be duplicated were those of a turbojet engine at high altitudes and with the afterburner operative.
Date: December 17, 1954
Creator: de Moraes, Carlos A.; Hagginbothom, William K., Jr. & Falanga, Ralph A.
Partner: UNT Libraries Government Documents Department
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Determination of Longitudinal Stability in Supersonic Accelerated Maneuvers for the Douglas D-558-II Research Airplane

Description: Report discussing testing of a Douglas D-558-II to investigate its longitudinal stability characteristics in accelerated flight at supersonic speeds. Information about the normal-force coefficients and their relation to stability and pitch-up of the aircraft is included.
Date: February 17, 1954
Creator: Ankenbruck, Herman O.
Partner: UNT Libraries Government Documents Department
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Drag and Heat Transfer on a Parabolic Body of Revolution (NACA RM-10) in Free Flight to Mach Number 2 With Both Constant and Varying Reynolds Number and Heating Effects on Turbulent Skin Friction

Description: Report discussing testing on a research model to obtain experimental drag and heat-transfer data under constant and varying conditions of Reynolds number and heating effects. Average body turbulent skin-friction-drag coefficients were determined for both constant and varying heating effect.
Date: June 17, 1954
Creator: Maloney, Joseph P.
Partner: UNT Libraries Government Documents Department
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Dual Channel Pulse Analyser and Count-Rate Meter for Gamma Spectrometer Monitor

Description: Describes the current prototype model of a linear amplifier, two-channel pulse-height analyser, two-channel count-rate meter, and count-rate difference detector for a gamma-ray spectrometer monitor developed to approach the above design criteria.
Date: June 17, 1954
Creator: Paul, R. S. & Wood, M. R.
Partner: UNT Libraries Government Documents Department
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Effect of ground interference on the aerodynamic and flow characteristics of a 42 degree sweptback wing at Reynolds numbers up to 6.8 x 10(6)

Description: Report presents the results of an investigation of the effects of ground interference on the aerodynamic characteristics of a 42 degree sweptback wing at distances 0.68 and 0.92 of the mean aerodynamic chord from the simulated ground to the 0.25-chord point of the mean aerodynamic chord. Survey data behind the wing, both with and without the simulated ground, are presented in the form of contour charts of downwash, sidewash, and dynamic-pressure ratio at longitudinal stations of 2.0 and 2.8 mea… more
Date: December 17, 1954
Creator: Furlong, G. Chester & Bollech, Thomas V.
Partner: UNT Libraries Government Documents Department
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The effect of stick-force gradient and stick gearing on the tracking accuracy of a fighter airplane

Description: Report presenting steady straight-and-level and steady turning tracking runs against an aerial target using an F-51H airplane equipped with a fixed optical sight and with various combinations of maneuvering stick-force and stick-deflection gradients. Results regarding aim wander, elevator movement, and stick-force variation for various test conditions are provided.
Date: December 17, 1954
Creator: Abramovitz, Marvin & Van Dyke, Rudolph D., Jr.
Partner: UNT Libraries Government Documents Department
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Effectiveness of boundary-layer removal near throat of ramp-type side inlet at free-stream Mach number of 2.0

Description: Report presenting the effect of removal of the boundary layer inside the inlet on the performance of a twin-duct side-air-intake system in the 8- by 6-foot supersonic wind tunnel at a free-stream Mach number of 2.0. Results regarding the internal performance characteristics of inlets, supercritical mass-flow ratio, diffuser total-pressure recovery, and effect of bleeding the boundary layer are provided.
Date: November 17, 1954
Creator: Obery, Leonard J. & Cubbison, Robert W.
Partner: UNT Libraries Government Documents Department
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Effects of Molecular Weight on Crazing and Tensile Properties of Polymethyl Methacrylate

Description: Memorandum reporting the tensile and crazing properties for five cast polymethy lmethacrylate sheets in which the molecular weight of the resin was 90,000, 120,000, 200,000, 490,000, and 3,160,000. Both stress crazing and stress-solvent crazing tests were conducted. Results regarding the standard tensile tests, stress-solvent crazing tests, and discussion of failure and crazing are provided.
Date: February 17, 1954
Creator: Wolock, I.; Sherman, M. A. & Axilrod, B. M.
Partner: UNT Libraries Government Documents Department
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Effects of rigid spoilers on the two-dimensional flutter derivatives of airfoils oscillating in pitch at high subsonic speeds

Description: Report presenting a study of the effects of spoilers with fixed heights equal to 2.5 to 4 percent of the airfoil chord on the aerodynamic lift and moment flutter derivatives of oscillating two-dimensional airfoils. Results regarding the typical effects of spoiler deflection, effects of Mach number, and aerodynamic torsional instability boundaries for fixed spoiler heights as affected by airfoil profile are provided.
Date: December 17, 1954
Creator: Monfort, James C. & Wyss, John A.
Partner: UNT Libraries Government Documents Department
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Flight Investigation of the Aerodynamic Derivatives and Performance of Control Systems of Two Full-Scale Guided Bombs

Description: Report presenting the aerodynamic stability derivatives and pitch and yaw control effectiveness of two full-scale guided bombs over a range of Mach numbers in free-flight drop tests. Results regarding performance information, roll control operation, and aerodynamic characteristics are provided.
Date: June 17, 1954
Creator: Seaberg, Ernest C. & Geller, Edward S.
Partner: UNT Libraries Government Documents Department
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Flight Investigation to Determine Lift and Drag Characteristics of a Canard Ram-Jet Missile Configuration in the Mach Number Range of 0.8 to 2.0

Description: Report presenting an investigation on a canard ramjet missile configuration to determine its lift and drag characteristics at low values of lift. Two rocket-boosted models that differed only in the size and deflection of the canard were used. Information about the trim lift characteristics, drag, and stability is provided.
Date: June 17, 1954
Creator: Gammal, Abraham A. & Kennedy, Thomas L.
Partner: UNT Libraries Government Documents Department
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Formation and Combustion of Smoke in Laminar Flames

Description: "The nature and formation of smoke and its combustion were investigated. Smoke, which consist of tiny mesomorphous crystals tightly packed into popcorn-ball-like particles that agglomerate to give filaments, was found to contain about 5 percent of the hydrogen originally present in the fuel. Factors affecting smoke formation were studied in both diffusion flames and premixed Bunsen flames. It is suggested that smoking tendency increases with increasing stability of the carbon skeleton of the mo… more
Date: August 17, 1954
Creator: Schalla, Rose L.; Clark, Thomas P. & McDonald, Glen E.
Partner: UNT Libraries Government Documents Department
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Investigation at Supersonic Speeds of the Effect of Jet Mach Number and Divergence Angle of the Nozzle Upon the Pressure of the Base Annulus of a Body of Revolution

Description: Report presenting an investigation in the 9-inch supersonic tunnel to determine the jet effects for varying jet Mach number and nozzle divergence angle upon the pressure on the base annulus of a model with a cylindrical afterbody. Testing occurred over a wide range of jet static pressure ratios and Mach numbers. Results regarding sonic jets and supersonic jets are provided.
Date: December 17, 1954
Creator: Bromm, August F., Jr. & O'Donnell, Robert M.
Partner: UNT Libraries Government Documents Department
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An Investigation of the Effects of Jet Exhaust and Reynolds Number Upon the Flow Over the Vertical Stabilizer and Rudder of the Douglas D-558-II Research Airplane at Mach Numbers of 1.62, 1.93, and 2.41

Description: Memorandum presenting an investigation to determine the effects of jet exhaust and Reynolds number on the flow over the vertical stabilizer and rudder of the Douglas D-558-II research airplane with special attention to an understanding of the rudder reversals experienced in flight on the full-scale airplane. Tests were made at Mach numbers of 1.62, 1.93, and 2.41 over a range of ratios of jet static pressure to stream static pressure from the jet-off ratio to about 40 and for a maximum range of… more
Date: June 17, 1954
Creator: Grigsby, Carl E.
Partner: UNT Libraries Government Documents Department
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An Investigation of the Hydrodynamic Characteristics of a 1/10-Size Powered Dynamic Model of the Martin M-267 Patrol-Type Seaplane with Two Forebody Configurations: TED No. NACA DE 376

Description: Report presenting an investigation of the hydrodynamic characteristics of a scale powered dynamic model of a patrol-type seaplane designed by the Glenn L. Martin Company. The seaplane had a high-aspect-ratio wing and a T-tail with an all-movable stabilizer. A comparison was made between two forebody configurations, one with a sharp forebody keel in cross section and the other with the forebody cross section rounded in the vicinity of the keel.
Date: August 17, 1954
Creator: Mottard, Elmo J. & Coffee, Claude W., Jr.
Partner: UNT Libraries Government Documents Department
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Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data

Description: Report presenting a wind-tunnel investigation of a model equipped with a 60 degree delta wing and a 60 degree delta horizontal all-movable canard control surface to determine the stability, control, and canard-surface hinge-moment characteristics at low speeds and at a Reynolds number of 9 x 10(exp 6). Two longitudinal positions of the canard surface were tested. Results regarding lift and pitching moment, drag, and hinge moment are provided.
Date: June 17, 1954
Creator: Burrows, Dale L.
Partner: UNT Libraries Government Documents Department
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Lateral Motions Encountered with the Douglas D-558-II All-Rocket Research Airplane During Exploratory Flights to a Mach Number of 2.0

Description: Memorandum presenting flight tests performed with the Douglas D-558-II research airplane in order to determine the lateral handling characteristics in straight flight at supersonic speeds. It primarily describes the lateral motions obtained at moderate and low angles of attack during a preliminary survey in pushovers and straight flight at supersonic Mach numbers up to about 2.0 at altitudes between 50,000 and 70,000 feet.
Date: December 17, 1954
Creator: Ankenbruck, Herman O. & Wolowicz, Chester H.
Partner: UNT Libraries Government Documents Department
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Measurement of the Static Stability and Control and the Damping Derivatives of a 0.13-Scale Model of the Convair XFY-1 Airplane, Ted No. NACA DE 368

Description: "An investigation has been conducted to determine the static stability and control and damping in roll and yaw of a 0.13-scale model of the Convair XFY-1 airplane with propellers off from 0 deg to 90 deg angle of attack. The tests showed that a slightly unstable pitch-up tendency occurred simultaneously with a break in the normal-force curve in the angle-of-attack range from about 27 deg to 36 deg. The top vertical tail contributed positive values of static directional stability and effective d… more
Date: October 17, 1954
Creator: Johnson, Joseph L., Jr.
Partner: UNT Libraries Government Documents Department
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Performance of a supersonic ramp inlet with internal boundary-layer scoop

Description: Report presenting an experimental investigation to determine the effect on inlet performance of several boundary-layer scoops mounted inside a ramp-type inlet in the 8 by 6-foot supersonic wind tunnel over a range of Mach numbers. Results regarding typical variations of inlet-diffuser pressure recovery, peak recovery, inlet stability range, and effect of inlet sizing are provided.
Date: November 17, 1954
Creator: Campbell, Robert C.
Partner: UNT Libraries Government Documents Department
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Progress report on the Happy Jack Mine, White Canyon area, San Juan County, Utah

Description: This report gives preliminary results of detailed mapping done during the 1952 field season, summarizes habits of the uranium deposits, and presents guides that may be useful in exploring for additional deposits.
Date: September 17, 1954
Creator: Trites, Albert F. & Chew, Randall T.
Partner: UNT Libraries Government Documents Department
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