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Strength of Welded Aircraft Joints

Description: "This investigation is a continuation of work started in 1928 and described in NACA-TR-348 which shows that the insertion of gusset plates was the most satisfactory way of strengthening a joint. Additional tests of the present series show that joints of this type could be improved by cutting out the portion of the plate between the intersecting tubes. T and lattice joints in thin-walled tubing 1 1/2 by 0.020 inch have somewhat lower strengths than joints in tubing of greater wall thickness because of failure by local buckling. In welding the thin-walled tubing, the recently developed "carburizing flux" process was found to be the only method capable of producing joints free from cracks" (p. 177).
Date: August 12, 1936
Creator: Brueggeman, W. C.
Partner: UNT Libraries Government Documents Department
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A study of the two-control operation of an airplane

Description: The two-control operation of a conventional airplane is treated by means of the theory of disturbed motions. The consequences of this method of control are studied with regard to the stability of the airplane in its unconstrained components of motion and the movements set up during turn maneuvers.
Date: August 12, 1936
Creator: Jones, Robert T.
Partner: UNT Libraries Government Documents Department
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Effect of Water-Alcohol Injection and Maximum Economy Spark Advance on Knock-Limited Performance and Fuel Economy of a Large Air-Cooled Cylinder

Description: An investigation was conducted to determine the effect of a coolant solution of 25 percent ethyl alcohol, 25 percent methyl alcohol, and 50 percent water by volume and maximum-economy spark advance on knock-limited performance and fuel economy of a large air-cooled cylinder. The knock-limited performance of the cylinder at engine speeds of 2100 and 2500 rpm was determined for coolant-fuel ratios of 0.0, 0.2, and 0.4. The effect of water-alcohol injection on fuel economy was determined in constant charge-air flow tests. The tests were conducted at a spark advance of 20 deg B.T.C. and maximum-economy spark advance.
Date: August 12, 1945
Creator: Heinicke, Orville H. & Vandeman, Jack E.
Partner: UNT Libraries Government Documents Department
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Preliminary investigation of spoiler lateral control on a 42 degree sweptback wing at transonic speeds

Description: Investigation at transonic speeds in the high-speed 7- by 10-foot tunnel to determine the rolling-effectiveness characteristics of a spoiler on a double-wedge-type semispan wing with a sweepback angle of 42 degrees. Results regarding the variation of rolling-moment coefficient, spoiler effectiveness, and rolling effectiveness are provided.
Date: August 12, 1947
Creator: Schneiter, Leslie E. & Ziff, Howard L.
Partner: UNT Libraries Government Documents Department
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Design and Performance of Experimental Axial-Discharge Mixed-Flow Compressor 1: Impeller Design Theory

Description: Memorandum presenting a description of an axial-discharge mixed-flow compressor, which is especially adapted for jet engines because of the large mass flow per unit frontal area. The best impeller was selected on the basis of the maximum air-flow capacity, which was 19.6 pounds per second for a 14-inch-diameter impeller with a tip speed of 1480 feet per second and a pressure ratio of 3.5.
Date: August 12, 1948
Creator: Goldstein, Arthur W.
Partner: UNT Libraries Government Documents Department
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Design and performance of experimental axial-discharge mixed-flow compressor 2: performance of impeller

Description: Report presenting an analysis of an axial-discharge mixed-flow compressor designed to combine the compactness, reliability, and wide operating range of a mixed-flow compressor with the high flow capacity per unit of frontal area that characterizes the axial-flow compressor. The primary objective of this design was to maximize the flow capacity for a predetermined pressure ratio. Results regarding the flow distribution at the impeller inlet, flow distribution at the impeller outlet, and impeller performance are provided.
Date: August 12, 1948
Creator: Wilcox, Ward W.
Partner: UNT Libraries Government Documents Department
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Natural Icing of an Axial-Flow Turbojet Engine in Flight for a Single Icing Condition

Description: Memorandum presenting an investigation in natural icing conditions to determine the effect of ice formations on the performance of an axial-flow turbojet engine. A description of the change over time in tail-pipe temperature, engine jet thrust, fuel flow, ice collection, and acceleration qualities are provided.
Date: August 12, 1948
Creator: Acker, Loren W.
Partner: UNT Libraries Government Documents Department
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Preliminary Theoretical and Flight Investigation of the Lateral Oscillation of the X-1 Airplane

Description: Report presenting the results of flight tests showing lateral oscillation in the Bell X-1 and calculations created to determine the effects of changes in several mass and aerodynamic parameters on the lateral oscillations. Calculations indicate that lateral stability should be improved by a more positive inclination of the principal axis of inertia or a reduction of the value of yawing moment of inertia.
Date: August 12, 1949
Creator: Drake, Hubert M. & Wall, Helen L.
Partner: UNT Libraries Government Documents Department
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The Static-Pressure Error of Wing and Fuselage Airspeed Installations of the X-1 Airplanes in Transonic Flight

Description: Memorandum presenting measurements made in the transonic speed ranges of the static-pressure position error at a distance of 0.96 chord ahead of the wing tip of both the 8-percent-thick-wing and the 10-percent-thick-wing X-1 airplanes, and at a point 0.6 maximum fuselage diameter ahead of the fuselage nose of the X-1 airplanes. Results regarding the accuracy of pitot-static heads, static-pressure error of wing-tip installation, static-pressure error of the fuselage-nose installation, and error in total pressure are provided.
Date: August 12, 1949
Creator: Goodman, Harold R. & Yancey, Roxanah B.
Partner: UNT Libraries Government Documents Department
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Supplementary Wind-Tunnel Investigation of the Stability of the Jettisonable Nose Section of the X-2 Airplane

Description: A supplementary investigation on the stabilization of the Jettisonable nose section of the X-2 airplane has been conducted in the Langley 20-foot free-spinning tunnel. It was found that the nose section could be stabilized by the addition of curved fins which could be folded against the fuselage for normal flight.
Date: August 12, 1949
Creator: Goodwin, Roscoe H.
Partner: UNT Libraries Government Documents Department
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Synthesis of Properties of Methylisoproplydiketone and 1,1 Dinitroisobutane and Their Analytical Determination in Hexone-Nitric Acid Systems

Description: Report discussing a study with the following objectives: "to synthesize pure specimens of both methylisoproplydiketone and 1,1 dinitroisobutane, to determine their physical and chemical properties, and to devise analytical methods which permit their quantitative determination in hexone-nitric acid systems to be encountered in the Redox Process."
Date: August 12, 1949
Creator: Wagner, Robert M.
Partner: UNT Libraries Government Documents Department
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Behavior of S.I.R. Fuels Irradiated in Sodium: Final Report, Production Test 105-180-P (Special Request KAPL-79: The "Beta Experiment")

Description: Report describing the effects of pile irradiation on fuel materials and coil springs for the Submarine Intermediate Reactor. The investigation was called for by Hanford Irradiation Request No. 79. Results of investigation are detailed in the report.
Date: August 12, 1952
Creator: Lambert, J. B., 1929-
Partner: UNT Libraries Government Documents Department
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Calibration of strain-gage installations in aircraft structures for the measurement of flight loads

Description: "A general method has been developed for calibrating strain-gage installations in aircraft structures, which permits the measurement in flight of the shear or lift, the bending moment, and the torque or pitching moment on the principal lifting or control surfaces. Although the stress in structural members may not be a simple function of the three loads of interest, a straightforward procedure is given for numerically combining the outputs of several bridges in such a way that the loads may be obtained. Extensions of the basic procedure by means of electrical combination of the strain-gage bridges are described which permit compromises between strain-gage installation time, availability of recording instruments, and data reduction time" (p. 1).
Date: August 12, 1952
Creator: Skopinski, T. H.; Aiken, William S., Jr. & Huston, Wilber B.
Partner: UNT Libraries Government Documents Department
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Heat Transfer and Pressure Loss in Tube Bundles for High Performance Heat Exchangers and Fuel Elements

Description: From introduction: "The tube arrangement covered in this report was proposed in June, 1950, as a means of halving the weight and volume required for the heat exchanger. Ideally, the pressure drop across this arrangement should be little more than that required to overcome the skin friction on the tube surfaces. If the pressure drop across the tube spacers and in the cross-flow regions can be kept low, this ideal can be approached. much of the test work covered in this report was devoted to this phase of the problem."
Date: August 12, 1952
Creator: Cohen, G. H.; Fraas, A. P. & LaVerne, M. E.
Partner: UNT Libraries Government Documents Department
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Influence of a canard-type control surface on the internal and external performance characteristics of nacelle-mounted supersonic diffusers (conical centerbody) at a rearward body station for a Mach number of 2.0

Description: Report presenting an investigation of the effects of the wake resulting from control-surface deflection on the internal performance of two supersonic diffusers and on the engine-body interference drag in the 8- by 6-foot supersonic wind tunnel at Mach number 2.0. Results regarding the internal-flow evaluation, high-pressure-recovery diffuser, and drag evaluation are provided.
Date: August 12, 1952
Creator: Obery, L. J. & Krasnow, H. S.
Partner: UNT Libraries Government Documents Department
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Longitudinal Stability, Trim, and Drag Characteristics of a Rocket-Propelled Model of an Airplane Configuration Having a 45 Degree Sweptback Wing and an Unswept Horizontal Tail

Description: Report discussing an investigation of the longitudinal stability, trim, and drag of a rocket-propelled model at low lift coefficients at a range of Mach numbers. the configuration included a wing and horizontal tail of aspect ratio 4 and thickness ratio in the streamwise direction of 6 percent.
Date: August 12, 1952
Creator: Parks, James H. & Kehlet, Alan B.
Partner: UNT Libraries Government Documents Department
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Mechanical development studies technical activities report, July 1952

Description: Described herein are studies on pile control, shielding, process tube assembly, pile operating equipment, pile renovation, power recovery, pile piping and the 189-D test laboratory at Hanford.
Date: August 12, 1952
Creator: Alexander, W. K.
Partner: UNT Libraries Government Documents Department
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Preliminary Air-Flow and Thrust Calibrations of Several Conical Cooling-Air Ejectors with a Primary to Secondary Temperature Ratio of 1.0, 2: Diameter Ratios of 1.06 and 1.40

Description: "An investigation was made of the performance of nine conical cooling-air ejectors at primary jet pressure ratios from 1 to 10, secondary pressure ratios to 4.0, and a temperature ratio of unity. This phase of the investigation was limited to conical ejectors having shroud exit to primary nozzle exit diameter ratios of 1.06 and 1.40, with several spacing ratios for each. The experimental results indicated that the pumping range and amount of cooling-air flow obtained with a 1.06 diameter ratio ejector were relatively small for cooling purposes but that the maximum possible thrust loss, which occurred with no secondary flow, was only 7 percent of convergent nozzle thrust" (p. 1).
Date: August 12, 1952
Creator: Greathouse, W. K. & Hollister, D. P.
Partner: UNT Libraries Government Documents Department
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Preliminary investigation of effect of angle of attack on pressure recovery and stability characteristics for a vertical-wedge-nose inlet at Mach number of 1.90

Description: Report presenting a preliminary investigation of a wedge-type compression surface mounted vertically in a circular cowling conducted in the supersonic wind tunnel at a Mach number of 1.90 and range of angles of attack. With symmetrical cowling, the pressure recovery and stability characteristics comparable to a conical inlet were obtained, but twin-duct flow interaction was observed. Results regarding the pressure recovery and stability characteristics and effects of removing the lower cowl lip and perforating the wedge centerbody are provided.
Date: August 12, 1952
Creator: Leissler, L. Abbott & Hearth, Donald P.
Partner: UNT Libraries Government Documents Department
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Effect of Temperature on Uranium Recovery Columns Operation

Description: Some data on the temperature effect in pulse columns are reviewed. New data obtained with the "vibrational" stirrer are reported. The effects on both the dispersion and coalescence and the net rate of extraction suggest that improved operation of the RA column and lowered waste losses would be expected at elevated temperatures.
Date: August 12, 1953
Creator: Burger, L. L.
Partner: UNT Libraries Government Documents Department
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SLUG PROGRAM QUARTERLY REPORT FOR APRIL, MAY, JUNE 1953

Description: Preliminary results are reported on the coating of U by immersion in nonreacting molten Mg saturated with Zr, Ni, or Si. A corrosion analysis of the resulting Mg-- Zr outer coat was performed on one failure occurring in boiling water. Further experiments are described on the corrosion testing of Cu-plated and Zn-dipped U. Improvements in the Zn-dip process are uncertain, however, because hot-dip Zn coats show comparable corrosion characteristics. Investigations have been conducted on the casting of U in cans of Zr,U, and Nb-- U alloys. Information was accumulated on the nature of the bonding characteristics, thermal treatment, and corrosion testing of such canning techniques. A new series of U-Nb alloys has been prepared for the purpose of studying the phase transformations of U. Data are given for the fabrication, phase characteristics, and physical and chemical properties of the series. Resistance-temperature curves were determined for U--Mo alloys, in addition to studies of corrosion and grain size in U--Zr--Hb alloys. A method is proposed for determining the thermal conductivity of U from diffusivity measurements. (C.H.)
Date: August 12, 1953
Creator: Chiotti, P. & Carlson, O.N.
Partner: UNT Libraries Government Documents Department
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