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Estimates of the Vertical-Tail Loads of a Bell P-63A-1 Airplane (AAF No. 42-68889) in Accelerated Rolling Maneuvers Based on Flight Tests With Two Vertical-Tail Arrangements

Description: Report discussing the results of using an enlarged vertical tail on a P-63A-1 on directional stability. The tests included measurements of the amount of sideslip at various speeds and normal accelerations. Potential required modifications for increased performance using the larger tail are also described.
Date: November 30, 1944
Creator: Johnson, Harold I.
Partner: UNT Libraries Government Documents Department
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Progress Report for the Month of November, 1947

Description: This is a progress report on the work of ore tressing and pyrometallurgical studies as well as a study of chemical work on phosphates. This report covers the month of November, 1947.
Date: November 30, 1947
Creator: Center, E. J.; Pray, H. A.; Richardson, A. C. & Sullivan, John D.
Partner: UNT Libraries Government Documents Department
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Berkeley Proton Linear Accelerator

Description: Construction of a linear accelerator which increases the energy of protons from a 4 Mev Van de Graaff injector to a final energy of 31.5 Mev.
Date: November 30, 1948
Creator: Alvarez, Luis W.; Bradner, Hugh; Gordon, Hayden; Panofsky, Wolfgang K. H.; Richman, Chaim & Woodyard, John R.
Partner: UNT Libraries Government Documents Department
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Electronics progress report

Description: The work to determine the feasibility of a pratical solution counter for alphas has been continued through this month. It has developed that the electronic technique using an Amperex mica-window GM tube (1.4 mg./cm{sup 2} mica) is reliable, and it now appears that the problem is mainly one of solution-mounting technique. Two four-input gamma mixers and three two-input B-wall mixers have been given a final check and assembled in cabinets with their associated scalers. These scalars, Instrument Development Laboratory Model 161-S, were modified for use with either type mixer and may also be used for straight GM counting. One Instrument Development Laboratory Model 161-S, scale of 256 gamma counter has been given performance tests before being placed in operation at Mound Laboratory. Tests are being run on the parallel plate alpha counter Model K-262.
Date: November 30, 1948
Creator: Heyd, J.W.
Partner: UNT Libraries Government Documents Department
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Flight and Wind-Tunnel Investigation to Determine the Aileron-Vibration Characteristics of 1/4-Scale Wing Panels of the Douglas D-558-2 Research Airplane

Description: Report presenting a flight and wind-tunnel investigation to determine the aerodynamic vibration characteristics of ailerons for the Douglas D-558-2 airplane. Testing was conducted to investigate the possibilities of a single-degree-of-freedom flutter known as aileron "buzz" or aileron compressibility flutter. Results regarding the three types of aileron vibration observed and vibration amplitudes are provided.
Date: November 30, 1948
Creator: Angle, Ellwyn E. & Lundstrom, Reginald R.
Partner: UNT Libraries Government Documents Department
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Simulated Altitude Performance of Combustor of Westinghouse 19XB-1 Jet-Propulsion Engine

Description: From Summary: "A 19XB-1 combustor was operated under conditions simulating zero-ram operation of the 19XB-1 turbojet engine at various altitudes and engine speeds. The combustion efficiencies and the altitude operational limits were determined; data were also obtained on the character of the combustion, the pressure drop through the combustor, and the combustor-outlet temperature and velocity profiles. At altitudes about 10,000 feet below the operational limits, the flames were yellow and steady and the temperature rise through the combustor increased with fuel-air ratio throughout the range of fuel-air ratios investigated. At altitudes near the operational limits, the flames were blue and flickering and the combustor was sluggish in its response to changes in fuel flow."
Date: November 30, 1948
Creator: Childs, J. Howard & McCafferty, Richard J.
Partner: UNT Libraries Government Documents Department
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Surface-Pressure Distributions on a Systematic Group of NACA 1-Series Cowlings With and Without Spinners

Description: "A method for calculating the flow fields of axially symmetric bodies from their pressure distributions is reported in NACA RM No. L8I17. In order to facilitate application of this method to the important case of the cowling-spinner combination, for use in the design of propellers, the present paper presents static-pressure distributions on the tops of 79 high-critical-speed NACA 1-series cowling-spinner combinations over wide ranges of inlet-velocity ratio at angles of attack of 0 degrees, 2 degrees, 4 degrees, and 6 degrees. Static-pressure distributions around the nose sections of several cowlings are given in greater detail to aid in estimating the pressures near the stagnation points and to show the effect of changes in the internal lip shape" (p. 1).
Date: November 30, 1948
Creator: Boswinkle, Robert W., Jr. & Keith, Arvid L., Jr.
Partner: UNT Libraries Government Documents Department
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Effect of tunnel configuration and testing technique on cascade performance

Description: "An investigation has been conducted to determine the influence of aspect ratio, boundary-layer control by means of slots and porous surfaces, Reynolds number, and tunnel end-wall condition upon the performance of airfoils in cascades. A representative compressor-blade section (the NACA 65-(12)(10) of aspect ratios of 1, 2, and 4 has been tested at low speeds in cascades with solid and with porous side walls. Two-dimensional flow was established in porous-wall cascades of each of the three aspect ratios tested; the flow was not two-dimensional in any of the solid-wall cascades" (p. 263).
Date: November 30, 1949
Creator: Erwin, John R. & Emery, James C.
Partner: UNT Libraries Government Documents Department
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Flight Investigations at High-Subsonic, Transonic, and Supersonic Speeds to Determine Zero-Lift Drag of Fin-Stabilized Bodies of Revolution having Fineness Ratios of 12.5, 8.91, and 6.04 and Varying Positions of Maximum Diameter

Description: Rocket-powered models were flown at high-subsonic, transonic, and supersonic speeds to determine the zero-lift drag of fin-stabilized parabolic bodies of revolution differing in fineness ratio and in position of maximum diameter. The present paper presents the results for fineness ratio 12.5, 8.91 and 6.04 bodies having maximum diameters located at stations of 20, 40, 60, and 80 percent of body length. All configurations had cut-off sterns and all had equal base, frontal, and exposed fin areas. For most of the supersonic-speed range models having their maximum diameters at the 60-percent station gave the lowest values of drag coefficient. At supersonic speeds, increasing the fineness ratio generally reduced the drag coefficient for a given position of maximum diameter.
Date: November 30, 1949
Creator: Hart, Roger G. & Katz, Ellis R.
Partner: UNT Libraries Government Documents Department
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Progress Report No. 39, Section 2: Reactor Physics

Description: Report discussing theoretical reactor physics, applied reactor physics, the Alpha Experiment, nuclear measurements, and shipboard reactor studies performed during October 1949 at the Knolls Atomic Power Laboratory.
Date: November 30, 1949
Partner: UNT Libraries Government Documents Department
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Spin-Tunnel Investigation of the Jettisoning of External Fuel Tanks in Spins

Description: "A spin-tunnel investigation has been made to determine the probability of external fuel tanks striking an airplane after being jettisoned in a spin. The investigation showed that for straight-wing fighter-type designs in any case in which jettisoning of tanks in a spin might aid spin recovery the tanks would probably clear all parts of the airplane" (p. 1).
Date: November 30, 1949
Creator: Berman, Theodore
Partner: UNT Libraries Government Documents Department
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Calculated Lift Distributions of a Consolidated Vultee B-36 and Two Boeing B-47 Airplanes Coupled at the Wing Tips

Description: Report presenting the calculated lift distributions and associated aerodynamic parameters for a Consolidated Vultee B-36 and two Boeing B-47 airplanes coupled at the wing tips for different angles of attack and deflections of the ailerons. Results regarding lifts, moments, and induced drags and the use of the data for calculating aerodynamic forces and equilibrium conditions are provided.
Date: November 30, 1950
Creator: Diederich, Franklin W. & Zlotnick, Martin
Partner: UNT Libraries Government Documents Department
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A preliminary flight investigation of the effects of vortex generators on separation due to shock

Description: Investigation of an airplane in flight to determine the effectiveness of vortex generators in preventing separation due to compressibility shock at full-scale Reynolds numbers. All of the arrangements of vortex generators tested delayed separation to higher Mach numbers or lift coefficients. More experimentation will be needed to determine the optimum arrangement of vortex generators.
Date: November 30, 1950
Creator: Lina, Lindsay J. & Reed, Wilmer H., III
Partner: UNT Libraries Government Documents Department
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The Preparation and Some Properties of a Uranium Hexafluoride-Sodium Fluoride Complex

Description: Report discussing "preparation of some stable complexes of uranium hexafluoride with sodium, potassium, and thallium fluorides...Such compounds, reported as stable in air and of low vapor pressure, offered promise as convenient sources of unoxygenated hexa-valent uranium without the difficulties associated with the use of uranium hexafluoride itself."
Date: November 30, 1950
Creator: Horton, Charles A.; Harris, Warren W.; Barr, John T. & Posey, J. C.
Partner: UNT Libraries Government Documents Department
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Progress Report on Refining of MgX and Other Uranium-Bearing Materials

Description: From abstract: "Results of tests investigating the effects of feed and scrub acidities on the extraction of uranium and contaminants from process slurries by tributyl phosphate-Gulfspray Naphtha in a Scheibel continuous extractor are described. Studies on the fractional precipitation of MgX from a dilute sulfuric acid system throw considerable light on the probable constitution of MgX. Further data on the effect of acidity on the extraction of molybdenum and vanadium into ethyl ether are presented.
Date: November 30, 1950
Creator: Ewing, R. A.; Belcher, R. L.; Kiehl, S. J., Jr. & Bearse, A. E.
Partner: UNT Libraries Government Documents Department
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Thermal Conductivity of Metal Interfaces

Description: The coefficients of thermal conductivity of aluminum-bismuth metal-to-metal bonds, and of aluminum and bismuth surfaces in contact under pressure, were measured.
Date: November 30, 1950
Creator: Heckman, R. A.
Partner: UNT Libraries Government Documents Department
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Application of a channel design method to high-solidity cascades and tests of an impulse cascade with 90 degrees of turning

Description: From introduction: "A technique for application of the channel design methods of reference 11 to the design of high-solidity cascades with prescribed velocity distributions as a function of arc length along the blade-element profiles is presented herein."
Date: November 30, 1951
Creator: Stanitz, John D. & Sheldrake, Leonard J.
Partner: UNT Libraries Government Documents Department
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Fixation of Carbon Dioxide by Barley Roots

Description: The uptake of carbon dioxide by plant roots preparations has been demonstrated by various authors. In addition to confirming the fact of fixation, I have investigated the effect of a number of factors involved and the compounds in which the absorbed carbon appears, using carbon-14.
Date: November 30, 1951
Creator: Poel, L. W.
Partner: UNT Libraries Government Documents Department
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Investigation of the liquid fluorine-liquid diborane propellant combination in a 100-pound-thrust rocket engine

Description: The experimental performance of liquid fluorine and liquid diborane was investigated in a 100-pound-thrust engine at a combustion pressure of 300 pounds per square inch absolute. Methods of handling and transporting liquid fluorine were developed. It was extremely difficult to obtain satisfactory operation because of the high flame speed and high combustion chamber temperatures. The maximum performance obtained was 280 pound seconds per pound, 88 percent of the theoretical maximum. The theoretical performance was recalculated with revised thermodynamic data, indicating a maximum specific impulse of 311 pound seconds per pound as compared with the previously reported value of 323.
Date: November 30, 1951
Creator: Ordin, Paul M.; Douglass, Howard W. & Rowe, William H.
Partner: UNT Libraries Government Documents Department
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