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Airfoil section characteristics as affected by protuberances

Description: From Introduction: "The present report deals with another phase of the investigation; that is, the effects on airfoil section characteristics of protuberances extending along the entire span from the airfoil surface."
Date: July 11, 1932
Creator: Jacobs, Eastman N.
Partner: UNT Libraries Government Documents Department
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Working Charts for the Determination of the Lift Distribution Between Biplane Wings

Description: "In this report are presented empirical working charts from which the distribution of lift between wings, that is the fraction of the total lift borne by each, can be determined in the positive lift range for any ordinary biplane cellule whose individual wings have the same profile. The variables taken directly into account include airfoil section, stagger, gap/chord ratio, decalage, chord ratio, and overhang. It is shown that the influence of unequal sweepback and unequal dihedral in upper and… more
Date: July 11, 1932
Creator: Kuhn, Paul
Partner: UNT Libraries Government Documents Department
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Summary of Drag Characteristics of Practical-Construction Wing Sections

Description: "The effect of several parameters on the drag characteristics of practical-construction wing sections have been considered and evaluated. The effects considered were those of surface roughness, surface waviness, compressive load, and de-icers. The data were obtained from a number of tests in the Langley two-dimensional low-turbulence tunnels" (p. 359).
Date: July 11, 1946
Creator: Quinn, John H., Jr.
Partner: UNT Libraries Government Documents Department
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Investigation of the I-40 Jet-Propulsion Engine in the Cleveland Altitude Wind Tunnel. V - Operational Characteristics, 5, Operational Characteristics

Description: An investigation has been conducted in the Cleveland altitude wind tunnel to determine the operational characteristics of the I-40 jet-propulsion engine over a range of pressure altitudes from 10,000 to 50,000 feet and ram-pressure ratios from 1.00 to 1.76. Engine operational data were obtained with the engine in the standard configuration and with various modifications of the fuel system, the electrical system, and the combustion chambers. The effects of altitude and airspeed on operating spee… more
Date: July 11, 1947
Creator: Golladay, Richard L. & Gendler, Stanley L.
Partner: UNT Libraries Government Documents Department
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Performance of J33-A-27 Turbojet-Engine Compressor 1: Over-all performance characteristics at equivalent impeller speeds from 6100 to 11,800 rpm

Description: The J33-A-27 compressor was operated at an inlet pressure of 14 inches of mercury absolute and ambient inlet temperature over a range of equivalent impeller speeds from 6100 to 11,800 rpm. At the design equivalent speed of 11,800 rpm, the J33-A-27 compressor had a peak pressure ratio of 4.40 at an equivalent weight flow of 105.7 pounds per second and a peak adiabatic temperature-rise efficiency of 0.745. The maximum equivalent weight flow at design speed was 113.5 pounds per second.
Date: July 11, 1949
Creator: Kovach, Karl & Osborn, Walter M.
Partner: UNT Libraries Government Documents Department
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Flight measurements with the Douglas D-558-II (BuAero No. 37974) research airplane : determination of the aerodynamic center and zero-lift pitching-moment coefficient of the wing-fuselage combination by means of tail-load measurements in the Mach num

Description: Report presenting flight measurements of aerodynamic tail loads made on the Douglas D-558-II from which the variation with Mach number of the wing-fuselage aerodynamic center, static-longitudinal-stability parameter, the tail load per g, and the zero-lift wing-fuselage pitching-moment coefficient determined up to Mach number 0.87.
Date: July 11, 1950
Creator: Mayer, John P.; Valentine, George M. & Mayer, Geraldine C.
Partner: UNT Libraries Government Documents Department
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Analysis of Meteorological Data Obtained During Flight in a Supercooled Stratiform Cloud of High Liquid-Water Content

Description: "Flight icing-rate data obtained in a dense and abnormally deep supercooled stratiform cloud system indicated the existence of liquid-water contents generally exceeding values in amount and extent previously reported over the midwestern sections of the United States. Additional information obtained during descent through a part of the cloud system indicated liquid-water contents that significantly exceeded theoretical values, especially near the middle of the cloud layer. The growth of cloud dr… more
Date: July 11, 1951
Creator: Perkins, Porter J. & Kline, Dwight B.
Partner: UNT Libraries Government Documents Department
open access

Contributions of wing, tail, and fuselage to the aerodynamic characteristics of a semispan model of a supersonic airplane configuration at transonic speeds from tests by the NACA wing-flow method

Description: Report presenting an investigation using the NACA wing-flow method at transonic speeds to determine the contributions of wing, tail, and fuselage to the aerodynamic characteristics of a semispan airplane model with a long slender fuselage and straight wing and tail of low aspect ratio with faired symmetrical double-wedge airfoil sections 4.6 percent of the chord in thickness. Results regarding the drag, pitching moment, downwash, and lift are provided.
Date: July 11, 1951
Creator: Silsby, Norman S. & McKay, James M.
Partner: UNT Libraries Government Documents Department
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System Analyses and Autopilot Design for Automatic Roll Stabilization of a Supersonic Pilotless Aircraft

Description: Memorandum presenting system analyses and autopilot design procedure for a supersonic pilotless aircraft with twin jet engines. The autopilots investigated were a gyro-actuated control, a gyro-actuated control with a rate-sensing device, and an electronic-hydraulic autopilot. Results regarding the airframe and gyro-actuated control system; airframe, gyro-actuated control, and rate servo; airframe and electronic-hydraulic autopilot; and contribution of method of analysis to system design are pro… more
Date: July 11, 1951
Creator: Zarovsky, Jacob
Partner: UNT Libraries Government Documents Department
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100 Areas water treatment specifications

Description: This memorandum discussed review of the data from tests using alum in the treatment of pile process water, and using activated silica as a coagulant aid during period of low water temperature, which shows that this method should be substituted for the present method of treating pile process water in all 100 Areas. It was recommended that the water treatment procedures and specifications attached to this memorandum be initiated as standard practice in all 100 Areas as soon as it is possible to m… more
Date: July 11, 1952
Creator: Greninger, A. B.
Partner: UNT Libraries Government Documents Department
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Control characteristics at transonic speeds of a linked flap and spoiler on a tapered 45 degrees sweptback wing of aspect ratio 3

Description: Report presenting an investigation at transonic speeds to determine the control characteristics of a linked flap and spoiler. The control consisted of a linked combination of a quarter-span inboard plug-type spoiler and a full-span flap. Results regarding the hinge-moment, pitching-moment, lift, and rolling-moment are provided.
Date: July 11, 1952
Creator: Lockwood, Vernard E. & Fikes, Joseph E.
Partner: UNT Libraries Government Documents Department
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Force characteristics in the submerged and planing condition of a 1/5.78-scale model of a hydro-ski-wheel combination for the Grumman JRF-5 airplane

Description: From Summary: "Force characteristics determined from tank tests of a 1/5.78-scale model of a hydro-ski-wheel combination for the Grumman JRF-5 airplane are presented. The model was tested in both the submerged and planing conditions over a range of trim, speed, and load sufficiently large to represent the most probable full-size conditions."
Date: July 11, 1952
Creator: Land, Norman S. & Pelz, Charles A.
Partner: UNT Libraries Government Documents Department
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An Investigation of the Low-Speed Longitudinal Stability Characteristics of a Swept-Wing Airplane Model With Two Modifications to the Wing-Root Plan Form

Description: Report presenting a wind-tunnel investigation to determine the effects of two wing-root leading-edge plan-form modifications, including a notched leading-edge fillet and a rounded leading-edge fillet, on the low-speed longitudinal stability characteristics of an airplane model with a 50.7 degree sweptback wing. Results regarding stability at zero lift, variation of stability with lift coefficient, and lift and drag characteristics are provided.
Date: July 11, 1952
Creator: Kemp, William B., Jr.
Partner: UNT Libraries Government Documents Department
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Further Studies on Large-Batch Melting of Uranium

Description: The following report focuses on an investigation made to determine if vacuum melting was an absolutely necessary step in the metallurgical process of melting and casting uranium.
Date: July 11, 1955
Creator: Rengstorff, George W. & Lownie, Harold W., Jr.
Partner: UNT Libraries Government Documents Department
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Radiological Sciences Department Quarterly Progress Report Research and Development Activities April - June, 1955

Description: This report constitutes the Quarterly Progress Report covering April-June 1955, for the Health Instruments Division research and development activities. Most of the studies described concern the biological fate, environmental transport of radioactive effluents, or development of instrumentation for radiation detection.
Date: July 11, 1955
Creator: Parker, H. M.
Partner: UNT Libraries Government Documents Department
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Comparison With Theory of Landing Impacts of a Model of a Seaplane Incorporating a Hydro-Ski With and Without a Shock Absorber

Description: Report presenting experimental data from calm- and rough-water landing impacts with a dynamic model of a seaplane incorporating a flat-bottom hydro-ski mounted on a rigid strut and on a shock-absorber strut. Results regarding the fixed-ski case and translating-ski case are provided.
Date: July 11, 1956
Creator: Hoffman, Edward L.
Partner: UNT Libraries Government Documents Department
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Lift and Drag of the Bell X-5 Research Airplane in the 45 Degree Sweptback Configuration at Transonic Speeds

Description: Memorandum presenting a flight investigation of the Bell X-5 variable-sweep research airplane in the 45 degree wing sweptback configuration over a range of Mach numbers. Lift and drag values are presented and a comparison is made with data obtained with a wing sweepback of 59 degrees.
Date: July 11, 1956
Creator: Nugent, Jack
Partner: UNT Libraries Government Documents Department
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Some Effects of Wing Fences on the Lateral Stability Derivatives of a 60 Degree Delta Wing Oscillating Continuously in Yaw

Description: Report presenting an investigation at low speed to determine some of the effects of wing fences on the lateral stability derivatives of a flat-plate 60 degree delta-wing model oscillating continuously in yaw. Results regarding the variation with angle of attack, effect of frequency, effect of amplitude, number of fences, and some effects of fence geometric characteristics are provided.
Date: July 11, 1956
Creator: Riley, Donald R.
Partner: UNT Libraries Government Documents Department
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Some experiments relating to the problem of simulation of hot jet engines in studies of jet effects on adjacent surfaces at a free-stream Mach number of 1.80

Description: Report presenting an investigation at a free-stream Mach number of 1.80 in a blowdown tunnel to study the effect on the pressure distribution of a zero-angle-of-attack wing surface when certain exhaust parameters of a hot turbojet engine are varied. Results regarding shock wave and pressure coefficients are provided.
Date: July 11, 1956
Creator: Bressette, Walter E.
Partner: UNT Libraries Government Documents Department
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Static longitudinal stability and control characteristics of a model of a 45 degree swept-wing fighter airplane at Mach numbers of 1.41, 1.61, and 2.01

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the static longitudinal stability and control characteristics of a model of a 45 degree swept-wing fighter airplane at three Mach numbers. The results indicate that the static margin, which was fairly constant through the lift range, decrease from 32 to 27 percent mean aerodynamic chord with increase in Mach number from 1.41 to 2.01.
Date: July 11, 1956
Creator: Driver, Cornelius & Foster, Gerald V.
Partner: UNT Libraries Government Documents Department
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Evaluation of Reactor Core Materials for a Gas-Cooled Reactor Experiment

Description: From introduction: "On February 1, 1956, Batelle was awarded a contract by the Army Reactor Branch (ARB) to select, develop, and test core materials which could be used successfully in conducting a Gas Cooled Reactor Experiment (GCRE). The prime objective of the GCRE would be to evaluate small portable reactor systems for military application...The present report is concerned with the GCRE activities at Batelle during approximately the 7 months' period following the first report of this series,… more
Date: July 11, 1957
Creator: Keller, Donald L.
Partner: UNT Libraries Government Documents Department
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Evaluation of Reactor Core Materials for a Gas-Cooled Reactor Experiment

Description: An evaluation of core materials for a gas-cooled reactor is being made. Work on the ZrH/sub n/ moderator has been confined to the high-hydrogen or delta- phase material. Methods for preparing sound hydride bodies of the highhydrogen composition have been developed. Both solid hydride and hydride powder compacts are being clad by a pressure-bonding technique. The hot hardness, tensile strength, thermal conductivity, thermal-expansion coefficient, and dissociation pressure of the delta-phase mate… more
Date: July 11, 1957
Creator: Keller, D. L.
Partner: UNT Libraries Government Documents Department
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