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  • Polymer and Materials Science  (443)
  • Aircraft Design, Testing and Performance  (14)
  • Seismology  (9)
  • FLUID MECHANICS AND HEAT TRANSFER  (8)
  • AERODYNAMICS  (7)
  • 42.75
  • 1950-1954  (481)
  • 1953  (481)
Collection
Keywords
Years
  • 1950-1954  (481)
Year
  • 1
    facet.materialart.
    Unknown
    In:  Trans. Am. Geophys. Union, Beijing, Pergamon, vol. 34, no. 3-4, pp. 785-791, pp. 1246
    Publication Date: 1953
    Keywords: Seismology ; Project report/description ; EOS
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  • 2
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    Unknown
    California Institute of Technology Pasadena
    In:  Seismological Laboratory Bulletin, Los Angeles California, 1 p., California Institute of Technology Pasadena, vol. 1951, no. 6, pp. 95, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1953
    Keywords: Earthquake catalog ; Seismology ; Seismicity
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  • 3
    facet.materialart.
    Unknown
    In:  Bull. Seism. Soc. Am., Los Angeles California, 1 p., California Institute of Technology Pasadena, vol. 43, no. 6, pp. 223-232, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1953
    Keywords: Velocity analysis ; Seismology ; Earth model, also for more shallow analyses ! ; BSSA
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  • 4
    facet.materialart.
    Unknown
    In:  Bull. Geol. Soc. Am., Los Angeles California, 1 p., California Institute of Technology Pasadena, vol. 64, no. 6, pp. 1525, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1953
    Keywords: Seismology ; Seismometer ; Teleseismic events ; Earthquake
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  • 5
    facet.materialart.
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    California Institute of Technology Pasadena
    In:  Seismological Laboratory Bulletin, Los Angeles California, 1 p., California Institute of Technology Pasadena, vol. 1952, no. 6, pp. 104, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1953
    Keywords: Earthquake catalog ; Seismology ; Seismicity
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  • 6
    facet.materialart.
    Unknown
    In:  Trans., Am. Geophys. Union, Los Angeles California, 1 p., California Institute of Technology Pasadena, vol. 34, no. 6, pp. 161-173, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1953
    Keywords: Micro seismicity ; Waves ; Seismology ; Meteorology ; NOISE ; EOS
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  • 7
    facet.materialart.
    Unknown
    In:  Bull. Geol. Soc. Am., Los Angeles California, 1 p., California Institute of Technology Pasadena, vol. 64, no. 6, pp. 1525, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1953
    Keywords: Low velocity layer ; Velocity analysis ; Seismology
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  • 8
    facet.materialart.
    Unknown
    Pacific Science Association
    In:  7th Congress Proceedings New Zealand (1949), vol. 2, Wellington, Pacific Science Association, vol. 10, no. GL-TR-89-0230, pp. 7-9, (ISBN 3-933346-037)
    Publication Date: 1953
    Keywords: Tectonics ; Seismology ; Geol. aspects
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  • 9
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    Unknown
    Nat. Acad. Sci.
    In:  Proceedings, vol. 39, Washington, Nat. Acad. Sci., vol. 10, no. GL-TR-89-0230, pp. 849-853, (ISBN 3-933346-037)
    Publication Date: 1953
    Keywords: Travel time ; Seismology ; P-waves
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  • 10
    Publication Date: 2019-05-29
    Description: Conference on aerodynamics of high speed aircraft
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-57121
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  • 11
    Publication Date: 2019-05-23
    Description: Drag measurements at low lift of four-nacelle aircraft configuration with longitudinal distribution of cross-sectional area conducive to low transonic drag rise
    Keywords: AERODYNAMICS
    Type: NACA-RM-L53E29
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  • 12
    Publication Date: 2019-06-28
    Description: Pressure-distribution measurements have been made on the fus elage of the Bell X- 1 research airplane. Data are presented for angles of attack from 2 deg. to 8 deg. during pull-ups at Mach numbers of about 0.78, 0.85, 0.88, and 1.02. The results of the investigation indicated that a large portion of the load carried by the fuselage was in the vicinity of the wing and may be attributed to wing-to-fuselage carryover. The presence of the wing from the 41 to 60 percent fuselage stations influenced the fuselage pressures from about 30 to 65 percent fuselage length at Mach numbers of approximat ely 0.78, 0.85, and 0.88, and from about 35 to 80 percent fuselage length at a Mach number of approximately 1.02. The fuselage contributed about 20 percent of the total airplane normal-force coefficient. The center of pressure of the fuselage load throughout the tests was located from 41 to 51 percent fuselage length, which corresponds to the forward half of the wing root-chord location.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L53I15
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  • 13
    Publication Date: 2019-06-28
    Description: A method has been proposed for predicting the effect of a rapid blade-pitch increase on the thrust and induced-velocity response of a helicopter rotor. General equations have been derived for the ensuing motion of the helicopter. These equations yield time histories of thrust, induced velocity, and helicopter vertical velocity for given rates of blade-pitch-angle changes and given rotor-angular-velocity time histories. The results of the method have been compared with experimental results obtained with a rotor mounted on the Langley helicopter test tower. The calculated and experimental results are in good agreement, although, in general, the calculated thrust-coefficient overshoots are about 10 percent greater than those obtained experimentally.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-3044
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  • 14
    Publication Date: 2019-06-28
    Keywords: AERODYNAMICS
    Type: NACA-RM-A53G08
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  • 15
    Publication Date: 2019-06-28
    Description: An analysis of combined heat and mass transfer from a flat plate has been made in terms of Prandtl t s simplified physical concept of the turbulent boundary layer. The results of the analysis show that for conditions of reasonably small heat and mass transfer, the ratio of the mass-and heat-transfer coefficients is dependent on the Reynolds number of the boundary layer, the Prandtl number of the medium of diffusion, and the Schmidt number of the diffusing fluid in the medium of diffusion. For the particular case of water evaporating into air, the ratio of mass-transfer coefficient to heat-transfer coefficient is found to be slightly greater than unity.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-TN-3045
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  • 16
    Publication Date: 2019-06-28
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-TN-2904
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  • 17
    Publication Date: 2019-06-28
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-TN-2903
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  • 18
    Publication Date: 2019-06-28
    Description: Calculations have been made for the icing limit of a diamond airfoil at zero angle of attack in terms of the stream Mach number, stream temperature, and pressure altitude. The icing limit is defined as a wetted-surface temperature of 320 F and is related to the stream conditions by the method of Hardy. The results show that the point most likely to ice on the airfoil lies immediately behind the shoulder and is subject to possible icing at Mach numbers as high as 1.4.
    Keywords: AERODYNAMICS
    Type: NACA-TN-2861
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  • 19
    Publication Date: 2019-06-28
    Keywords: AERODYNAMICS
    Type: NACA-RM-E53C26
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  • 20
    Publication Date: 2019-06-28
    Description: The effects of primary and. runback icing and frost formations on the drag of an 8-foot-chord NACA 651-212 airfoil section were investigated over a range of angles of attack from 20 to 80 and airspeeds up to 260 miles per hour for icing conditions with liquid-water contents ranging from 0.25 to 1.4 grams per cubic meter and datum air temperatures of -30 to 30 F. The results showed that glaze-ice formations, either primary or runback, on the upper surface near the leading edge of the airfoil caused large and rapid increases in drag, especially at datum air temperatures approaching 32 F and in the presence of high rates of water catch. Ice formations at lower temperatures (rime ice) did not appreciably increase the drag coefficient over the initial (standard roughness) drag coefficient. Cyclic de-icing of the primary Ice formations on the airfoil leading-edge section permitted the drag coefficient to return almost to the bare airfoil drag value. Runback icing on the lower surface did not present a serious drag problem except when heavy spanwise ridges of runback ice occurred aft of the heatable area. Frost formations caused rapid and large increases in drag with incipient stalling of the airfoil.
    Keywords: AERODYNAMICS
    Type: NACA-TN-2962
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  • 21
    Publication Date: 2019-06-28
    Description: Convective heat-transfer coefficients in dry air were obtained for an ellipsoidal spinner of 30-inch maximum diameter for both stationary and rotating operation over a range of conditions including airspeeds up to 275 miles per hour, rotational speeds up to 1200 rpm, and angles of attack of zero and 40 The results are presented in terms of Nusselt numbers, Reynolds numbers, and convective heat-transfer coefficients. The studies included both uniform heating densities over the spinner and uniform surface temperatures.. In general, the results showed that rotation will increase the convective heat transfer from a spinner, especially in the turbulent-flow regions. Rotation of the spinner at 1200 rpm and at a free-stream velocity of 275 miles per hour increased the Nusselt number parameter in the turbulent-flow region by 32 percent over that obtained with a stationary spinner; whereas in the nose region, where the flow was laminar, an increase of only 18 percent was observed. Transition from laminar to turbulent flow occurred over a large range of Reynolds numbers primarily because of surface roughness of the spinner. Operation at an angle of attack of 40 had only small effects on the local convective heat transfer for the model studied.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-RM-E53F02
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  • 22
    Publication Date: 2019-06-28
    Description: The effects of existing frictional heating were analyzed to determine the conditions under which ice formations on aircraft surfaces can be prevented. A method is presented for rapidly determining by means of charts the combination of-Mach number, altitude, and stream temperature which will maintain an ice-free surface in an icing cloud. The method can be applied to both subsonic and supersonic flow. The charts presented are for Mach numbers up to 1.8 and pressure altitudes from sea level to 45,000 feet.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-TN-2914
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  • 23
    Publication Date: 2019-06-28
    Description: The general effect of wing sweep on cloud-droplet trajectories about swept wings of high aspect ratio moving at subsonic speeds is discussed. A method of computing droplet trajectories about yawed cylinders and swept wings is presented, and illustrative droplet trajectories are computed. A method of extending two-dimensional calculations of droplet impingement on nonswept wings to swept wings is presented. It is shown that the extent of impingement of cloud droplets on an airfoil surface, the total rate of collection of water, and the local rate of impingement per unit area of airfoil surface can be found for a swept wing from two-dimensional data for a nonswept wing. The impingement on a swept wing is obtained from impingement data for a nonswept airfoil section which is the same as the section in the normal plane of the swept wing by calculating all dimensionless parameters with respect to flow conditions in the normal plane of the swept wing.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-TN-2931
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  • 24
    Publication Date: 2019-06-28
    Description: Trajectories were determined for droplets in air flowing through 90 deg elbows especially designed for two-dimensional potential motion with low pressure losses. The elbows were established by selecting as walls of each elbow two streamlines of the flow field produced by a complex potential function that establishes a two-dimensional flow around a 90 deg bend. An unlimited number of elbows with slightly different shapes can be established by selecting different pairs of streamlines as walls. The elbows produced by the complex potential function selected are suitable for use in aircraft air-intake ducts. The droplet impingement data derived from the trajectories are presented along with equations in such a manner that the collection efficiency, the area, the rate, and the distribution of droplet impingement can be determined for any elbow defined by any pair of streamlines within a portion of the flow field established by the complex potential function. Coordinates for some typical streamlines of the flow field and velocity components for several points along these streamlines are presented in tabular form.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-TN-2999
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  • 25
    Publication Date: 2019-06-28
    Description: The trajectories of droplets in the air flowing past an NACA 65A004 a irfoil at an angle of attack of 4 deg were determined. The amount of water in droplet form impinging on the airfoil, the area of droplet impingement, and the rate of droplet impingement per unit area on the airfoil surface were calculated from the trajectories and presented to cover a large range of flight and atmospheric conditions. The effect of a change in airfoil thickness from 12 to 4 percent at 4 deg angle of attack is presented by comparing the impingement calculations for the NACA 65A004 airfoil with those for the NACA 65(sub 1)-208 and 65(sub 1)-212 airfoils. The rearward limit of impingement on the upper surface decreases as the airfoil thickness decreases. The rearward limit of impingement on the lower surface increases with a decrease in airfoil t hickness. The total water intercepted decreases as the airfoil thickness is decreased.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-TN-3047
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  • 26
    Publication Date: 2019-06-28
    Description: An investigation has been made in the NACA Lewis icing research tunnel to determine the aerodynamic and icing characteristics of a full-scale induction-system air-scoop assembly incorporating a flush alternate inlet. The flush inlet was located immediately downstream of the offset ram inlet and included a 180 deg reversal and a 90 deg elbow in the ducting between inlet and carburetor top deck. The model also had a preheat-air inlet. The investigation was made over a range of mass-air- flow ratios of 0 to 0.8, angles of attack of 0 and 4 deg airspeeds of 150 to 270 miles per hour, air temperatures of 0 and 25 F various liquid-water contents, and droplet sizes. The ram inlet gave good pressure recovery in both clear air and icing but rapid blockage of the top-deck screen occurred during icing. The flush alternate inlet had poor pressure recovery in both clear air and icing. The greatest decreases in the alternate-inlet pressure recovery were obtained at icing conditions of low air temperature and high liquid-water content. No serious screen icing was observed with the alternate inlet. Pressure and temperature distributions on the carburetor top deck were determined using the preheat-air supply with the preheat- and alternate-inlet doors in various positions. No screen icing occurred when the preheat-air system was operated in combination with alternate-inlet air flow.
    Keywords: AERODYNAMICS
    Type: NACA-RM-E53E07
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  • 27
    Publication Date: 2019-07-11
    Description: An investigation was made to determine the static longitudinal and lateral stability and control characteristics of a l/6-scale model of the revised Republic XF-84H airplane with and without the propeller operating. The model had a 40deg swept wing of aspect ratio 3.45 and was equipped with a thin, three-blade supersonic-type propeller. Modifications incorporated in the revised model included a raised horizontal tail, increased rudder size, wing fences at 65 percent semispan, and a modified wing leading edge outboard of the fences. The test results for flap-retracted and flap-deflected conditions indicated that the revised configuration should be satisfactory for most normal flight conditions provided the angle of attack does not exceed the angle for pitch-up. An abrupt pitch-up tendency of the model was evident for the zero thrust condition above approximately 15' angle of attack. Although the effects of power were destabilizing, power-on longitudinal stability was satisfactory through the angle-of-attack range for which the model was stable with zero thrust. Above the angle of attack for pitch-up, an uncontrollable left roll-off tendency would be expected with power on and slats retracted. Projection of wing slats or use of leading-edge chord-extensions with only the left extension drooped were found beneficial in controlling the roll-off tendency with power on; however the most effective means found was projection of only the left slat.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL53I24
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  • 28
    Publication Date: 2019-07-12
    Description: A limited investigation of a 1/24-scale dynamically similar model of the Navy Bureau of Aeronautics DR-77 design was conducted in Langley tank no. 2 to determine the calm-water take-off and the rough-water landing characteristics of the design with particular regard to the take-off resistance and the landing accelerations. During the take-off tests, resistance, trim, and rise were measured and photographs were taken to study spray. During the landing tests, motion-picture records and normal-acceleration records were obtained. A ratio of gross load to maximum resistance of 3.2 was obtained with a 30 deg. dead-rise hydro-ski installation. The maximum normal accelerations obtained with a 30 deg. dead-rise hydro-ski installation were of the order of 8g to log in waves 8 feet high (full scale). A yawing instability that occurred just prior to hydro-ski emergence was improved by adding an afterbody extension, but adding the extension reduced the ratio of gross load to maximum resistance to 2.9.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL53F04
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  • 29
    Publication Date: 2019-07-11
    Description: A free-flight 0.12-scale rocket-boosted model of the North American MX-770 (X-10) missile has been tested in flight by the Pilotless Aircraft Research Division of the Langley Aeronautical Laboratory. Drag, longitudinal stability, and duct performance data were obtained at Mach numbers from 0.8 to 1.7 covering a Reynolds number range of about 9 x 10(exp 6) to 24 x 10(exp 6) based on wing mean aerodynamic chord. The lift-curve slope, static stability, and damping-in-pitch derivatives showed similar variations with Mach number, the parameters increasing from subsonic values in the transonic region and decreasing in the supersonic region. The variations were for the most part fairly smooth. The aerodynamic center of the configuration shifted rearward in the transonic region and moved forward gradually in the supersonic region. The pitching effectiveness of the canard control surfaces was maintained throughout the flight speed range, the supersonic values being somewhat greater than the subsonic. Trim values of angle of attack and lift coefficient changed abruptly in the transonic region, the change being associated with variations in the out-of-trim pitching moment, control effectiveness, and aerodynamic-center travel in this speed range. Duct total-pressure recovery decreased with increase in free-stream Mach number and the values were somewhat less than normal-shock recovery. Minimum drag data indicated a supersonic drag coefficient about twice the subsonic drag coefficient and a drag-rise Mach number of approximately 0.90. Base drag was small subsonically but was about 25 percent of the minimum drag of the configuration supersonically.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL53D10A
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  • 30
    Publication Date: 2019-07-11
    Description: An application of airfoil design methods was used to design series of related turbine-blade profiles to satisfy the conditions of inlet flow angle and turning angle encountered in the usual range of turbine operation. A series of blade profiles applicable to most turbine blading requirements and a secondary series with particular reference to impulse conditions were designed. Five blade sections from these series ranging in mean-line turning angles from 63 deg. to 120 deg. were tested in low-speed cascade tunnels. From low-speed test results optimum blade angles of attack were selected at each test condition. The induced angle and the deviation angle of the flow were determined from the low-speed data. If these angles are known for the solidity and inlet angle of an application, the necessary camber is specified. A method of predicting high-speed pressure distributions from low-speed cascade test results is presented to extend the usefulness of the low-speed data. Sample high-speed tests of two of the five blade sections were made at Mach numbers up to the critical value. The results indicated satisfactory flow conditions in all of the blade passages tested.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L53G15
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  • 31
    Publication Date: 2019-08-28
    Description: A systematic research program is being carried out in the Langley high-speed 7- by 10-foot tunnel to determine the aerodynamic characteristics of various arrangements of the component parts of research-type airplane models, including some complete model configurations. Data are being obtained on characteristics in pitch, sideslip, and during steady roll at Mach numbers from 0.40 to about 0.95. This paper presents results which show the effect of taper ratio on the aerodynamic characteristics in sideslip of wing-fuselage combinations having wings with a sweep of 45 degrees at the quarter-chord line, an aspect ratio of 4, and a NACA 65A006 airfoil section.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L53B25a
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  • 32
    Publication Date: 2019-07-11
    Description: An investigation has been made in the Langley 9- by 12-inch supersonic blowdown tunnel to determine the effects of external-store location on the lift, drag, and pitching-moment characteristics of a 45 degree sweptback wing at Mach numbers of 1.41, 1.62, and 1.96. The spanwise, chordwise, and vertical location of a Douglas-Aircraft Company, Inc., store of fineness ratio 8.58 was systematically varied over the outer 60 percent of the wing semispan. A brief investigation of strut sweep angle was also made. The test Reynolds number based on the wing mean aerodynamic chord ranged from 1.3 x 10(exp 6) to 1.5 x 10(exp 6).
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L52J27
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  • 33
    Publication Date: 2019-07-11
    Description: Preliminary results of one phase of a control-motion study program involving several jet fighter-type airplanes are presented in time-history form and are summarized as maximum measured quantities plotted against indicated airspeed. The results pertain to approximately 1,000 maneuvers performed by a Republic F-84G jet-fighter airplane during squadron operational training. The data include most tactical maneuvers of which the F-84G airplane is capable. Maneuvers were performed at pressure altitudes of 0 to 30,000 feet with indicated airspeeds ranging from the stalling speed to approximately 515 knots.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L53C27
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  • 34
    Publication Date: 2019-07-11
    Description: An experimental investigation has been conducted to determine the dynamic stability and control characteristics of a 0.13-scale free-flight model of the Convair XFY-1 airplane in test setups representing the setup proposed for use in the first flight tests of the full-scale airplane in the Moffett Field airship hangar. The investigation was conducted in two parts: first, tests with the model flying freely in an enclosure simulating the hangar, and second, tests with the model partially restrained by an overhead line attached to the propeller spinner and ground lines attached to the wing and tail tips. The results of the tests indicated that the airplane can be flown without difficulty in the Moffett Field airship hangar if it does not approach too close to the hangar walls. If it does approach too close to the walls, the recirculation of the propeller slipstream might cause sudden trim changes which would make smooth flight difficult for the pilot to accomplish. It appeared that the tethering system proposed by Convair could provide generally satisfactory restraint of large-amplitude motions caused by control failure or pilot error without interfering with normal flying or causing any serious instability or violent jerking motions as the tethering lines restrained the model.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL54B16A
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  • 35
    Publication Date: 2019-07-11
    Description: An experimental investigation has been made in the Langley stability tunnel at low speed to determine the static longitudinal and lateral stability characteristics of a l/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient were investigated for the complete model and for certain components of the model. Effects of control deflections and of propeller-blade angle were investigated briefly for the complete model. Most of the tests were made through an angle-of-attack range from about -4 deg. to 29 deg, and the thrust-coefficient range was from 0 t o 0.7. In order to expedite distribution of these data to interested persons, no analysis of the data has been prepared for this report,
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL53B20
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  • 36
    Publication Date: 2019-07-11
    Description: The hydrodynamic characteristics of a preliminary design of the Martin XP6M-1 flying boat have been determined. Longitudinal stability during take-off and landing, resistance of the complete model, and behavior during taxiing and landing in rough water are presented.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL53K06
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  • 37
    Publication Date: 2019-07-12
    Description: Static tests on a segment of a transpiration-cooled turbine rotor blade with a wire-cloth shell were conducted to determine the flow coefficients associated with some representative metering orifices. Average flow coefficients from 0.96 to 0.79 were obtained for orifices of 0.031 to 0.102 inch diameter.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E53L30a
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  • 38
    Publication Date: 2019-07-12
    Description: An investigation has been made at high subsonic speeds of the aerodynamic'characteristics in pitch and sideslip of a l/l4-scale model of the Grumman XF10F airplane with a wing sweepback angle of 42.5. The longitudinal stability characteristics (with the horizontal tail fixed) indicate a pitch-up near the stall; however, this was somewhat alleviated by the addition of fins to the side of the fuselage below the horizontal tail. The original model configuration became directionally unstable for small sideslip angles at Mach numbers above 0.8; however, the instability was eliminated by several different modifications.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL53G20
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  • 39
    Electronic Resource
    Electronic Resource
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 2-4 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Description / Table of Contents: The Prevention of Corrosion by Dehydration of the AtmosphereThe rusting of machine elements and parts and the formation of mildew on walls and ceilings is due to an excess of moisture in the surrounding air. Hence, in locations where, as a results of the process being carried out, large quantities of stream or vapour escape into the air surrounding the equipment, the consequent disadvantages can only be mitigated by the use of a suitably designed air dehydration plant. Enamelling of machinery, ceilings or walls is only a partial solution to the problem. The basic theoretical principles of air dehydration are then discussed, and some practical applications of these principles given. The introduction of warm air and the extraction of moist air are always necessary. The quantities and temperature of the incoming air, as well as the amount of heat required, are regulated by local conditions. Some numerical problems in the calculation of the individual values are solved by the use of an i-x diagram for moist air.
    Notes: Rosten von Maschinenenteilen und Schimmelbildung an Wäden und Decken ist eine Folge zu hoher Luftfeuchtigkeit. Deshalb können dort, wo durch den Arbeitsprozesse größere Dampf-bzw. Schwadenmengen in den Raum gelangen, die Übelstände nur durch eine zweckentsprechende Entnebelungsanlage behoben werden. Lackierungen von Maschinen, Decken oder Wänden bringen nur Teilerfolge. Nachfolgend werden die theoretischen Grundlagen der Entnebelung behandelt und im Anschluß daran an praktischen Beispielen deren zweckmäßige Durchführung. Stets ist die Zuführung von Warmluft und die Abführung von Feuchtluft erforderlich, wobei sich die notwendigen Lufttemperaturen und Mengen sowie die aufzuwendende Wärme nach den betrieblichen Gegebenheiten richten. An Zahlenbeispielen wird unter Benutzung eines i-x-Diagrammes für feuchte Luft die Berechnung der einzelnen Größen gezeigt.
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 48-48 
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    Keywords: Chemistry ; Polymer and Materials Science
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 119-119 
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 20-21 
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 1-1 
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 4-14 
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    Description / Table of Contents: The Influence of Impurities on the Resistance to Corrosion of Aluminium and its AlloysIt may be deduced generally from the present experiments that the resistance to corrosion of the metal. The influence of impurities is determined by the type of corrosive medium to which the metal is subjected, and, frequently, the failure of aluminium may be due more often to the influence of operating or other exterior conditions than to impurities in the metal itself.As a result of the examination of the tendencies to corrosion due to the individual impurities and small additions of foreign elements, it has been found that iron and copper exercise a harmful effect, although the effect of the iron can be greatly reduced by the addition of manganese. Silicon in solid solution is absolutely harmless, but when it is eliminated in elementary form, the powers of resistance of aluminium are reduced. Suitable heat treatment enables up to 0,5% Si. to be retained in solid solution. According to the latest investigations, the proportion of Fe. to Si. does not appear to be of particular importance to the resistance of aluminium to corrosion. Magnesium, lead, zinc and titanium in the amounts usually present in aluminum are harmless, but nickel is always injurious. Calcium and sodium, which often appear as impurities in aluminium obtained from certain ores, also influence the resistance to corrosion.The final conclusions obtained from the date on the influence of the addition of small quantities of other elements are, in most cases, not given, as the observations and results have mostly been obtained form single experiments, and, hence, do not offer sufficient material for the formation of conclusions that might be of practical value.
    Notes: Auf Grund der vorliegenden Versuchsergebnisse kann ganz allgemein gefolgert werden, daß der Korrosionswiderstand von Reinaluminium mit steigendem Reinheitsgrad zunimmt. Der Einfluß der Verunreinigungen wird bestimmt von der Art des Korrosionsmediums und oft wird das Versagen von Aluminium mehr auf die Einflüsse der vorliegenden Betriebsbedingungen bzw. seiner Umgebung als auf den der Verunreinigungen selbst zurückzuführen sein.Bei der Betrachtung der einzelnen Verunreinigungen und geringen Zusätze an fremden Elementen hinsichtlich ihrer Korrosionsbeeinflussung ergibt sich, daß Eisen und Kupfer einen schädlichen Einfluß ausüben, wobei jedoch die Wirkung des Eisens durch Zugabe von Mangan stark verringert werden kann. Silizium ist in fester Lösung völlig unschädlich, in elementarer Form ausgeschieden verringert es die Beständigkeit des Aluminium. Durch geeignete Wärmebehandlung gelingt es jedoch, bis zu 0,5% Si in fester Lösung zu halten. Das Verhältnis Fe:Si scheint nach den neueren Auffassungen für das Korrosionsverhalten von Aluminium nicht von besonderer Wichtigkeit zu sein. Magnesium, Zink, Blei und Titan sind in Gehalten, wie sie üblicherweise im Aluminium vorkommen, unschädlich, dagegen ist Nickel in jedem Falle schädlich. Auch Calcium und Natrium, die oftmals in aus bestimmten Erzen hergestelltem Aluminium als Verunreinigungen auftreten, beeinträchtigen dessen Korrosionsbeständigkeit.Bei den Angaben über den Einfluß von geringen Zusätzen weniger üblicher Elemente werden die daraus gezogenen Schlußfolgerungen in den meisten Fällen nicht wiedergeben, da die Beobachtungen überwiegend bei Einzelversuchen gemacht worden sind und demzufolge zu wenig Beweismaterial bieten für endgültige Rückschlüsse, die für die Praxis von Bedeutung sein könnten.
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 33-37 
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 47-47 
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 113-117 
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 48-48 
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 48-48 
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 247-248 
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    Description / Table of Contents: The Protective Action of cement against RustOf the various types od cements and concretes to be found on the market, Portland cement mixed with trass, pumice concrete and gypseous slag cement are particularly favourable to the formation of rust. The protective value of these building materials depends more on their pH value than on the thickness of the setting. Concrete for use in steel constructional work must normally contain a minimum of 30 Kgs of cement per cubic metre. The “Provisional” protection of the metal against rust by the application of a thin coating of cement slurry has not always proved successful, particularly in cases where a high degree of exposure was encountered. It would appear that a priming coat of red lead is to be recommended. Experience has proved that a coat of the cheaper variety of red lead known as “V 40” without the application of any additional coats of anti-corrosive paint, will protect the metal for periods of four and a half removed by the use of an autogenous burner.
    Notes: Unter den Handelssorten des Zements und Betons sind mit Traß versetzter Portlandzement, Bimsbeton und Gipsschlackenzement besonders zur chemischen Rostumwandlung befähigt. Der Schutzwert dieser Baustroffe wird mehr von ihrem pH-Wert als von der Dicke der Einbettung beeinflußt. Im Stahlbau verwendeter Beton muß in der Regel mindestens 300kg/m3 Zement enthateln. Der „ vorläufige“ Rostschutz durch Aufbringen dünner Zementschlämme hat sich in Fällen höherer Beanspruchung nicht durchweg bewährt. Es erscheint sodann eine einmalige Grundierung mit Bleimennige empfehlenswert, deren billigere Beisorte “V 40” das Eissen erwiesenermaßen auch ohne schützenden Deckanstrich 4½ Jahre und länger gegen Rostbildung zu schützen vermag. Alte Anstriche werden vor dem Einbetonieren am besten mit autogenen Flammstrahlern entfernt.
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 81-86 
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    Description / Table of Contents: On the “Sweating” of paper and its effect on Iron Goods packed in such PapersWhen paper is stored in the usual storage cellars, it can contain considerable quantities of water (e.g. 10%) this water content can lead to the formation of “sweat” at corresponding temperature changes. This, in turn can lead to iron goods packed in such paper rusting. A series of test investigated the formation of “sweat” under varying conditions. In order to reduce the formation of rust from this cause it is recommended that only paper that has been stored “dry” (i.e. at less than 65% relative humidity ) should be used for packing iron goods.
    Notes: Papier kann bei Lagerung in normalen Lagerkellern erhebliche Mengen lose gebundenen Wassers (Z.b. 10%) enthalten Dieser Wassergehalt kann bei entsprechenden Temperaturschwankungen zur Bildung von Schwitzwasser führen, wodurch die Gefahr der Verrostung verpackter eiserner Gegenstände stark erhöht wird. In einer Reihe von Versuchen wird die Abhängigkeit dieser Schwitzwasserbildung von den einzelnen Umständen näher verfolgt. Zur Herabsetzung der Verrostungsgefahr wird empfohlen für die Verpackung eiserner Gegenstände Papier zu verwenden, dass möglichst trocken (z. B. bei weniger als 65% relativer Luftfeuchtigkeit) gelagert hat.
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 397-399 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Description / Table of Contents: Heat-resisting Materials and CermetsCommencing with one or two historical facts, the article continues with a brief survey of the methods, such as silifications, are patterned on the Sherardisation process. The special alloys often contain Ni, Cr, Co, Mo and W. The latest materials, the cermets, occupy a place midway between ceramic materials and metals, and combine the advantageous qualities of both groups in such a way that they stil afford protection at temperatures in excess of 1,000°C.
    Notes: Ausgehend von einigen historischen Angaben wird ein Überblick über die Fabrikation hochhitzebeständiger Werkstoffe gegeben. Die einschlägigen Diffusionsmethoden, die Inkromierung und Silicierung knüpfen dabei an das Vorbild des Sherardisierens an. Die Sonderlegierungen enthalten vielfach Ni, Cr, Co, Mo, W usw. Die neuesten Werkstoffe, die Cermets, stehen zwischen den keramischen Massen und Metallen und verknüpfen die vorteilhaften Eigenschaften beider so wirksam, daß sie noch bei ü 1000°C Schutz gewähren.
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 413-421 
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    Keywords: Chemistry ; Polymer and Materials Science
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 423-424 
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    Keywords: Chemistry ; Polymer and Materials Science
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 426-426 
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    Keywords: Chemistry ; Polymer and Materials Science
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 428-428 
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    Keywords: Chemistry ; Polymer and Materials Science
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 334-334 
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    Keywords: Chemistry ; Polymer and Materials Science
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953) 
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    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 442-446 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Description / Table of Contents: Artifical Resins and Body TissuesThe article opens with a brief description of the irritational effects (corrosion, electrolysis, etc.), of metals entering and remaining in the human body, either, as a result of surgical treatment or accidently. The cause and effect of the irritation set up by foreign bodies is then discussed.It has been found that, in actual practice, there are artifical resins which have no effect upon human tissue. They must be chemically stable, cause no irritation of a mechanical nature and must have the physical properties of an insulator.When artifical resins are required to function statically in the human body, certain peculiar difficulties arise, which are due to the physical and chemical properties of the resin. These difficulties are described in detail.It is fact that artifical resin manufactures have not yet been able to produce a resin of a “universal” nature, which can be used as a statically functioning substitute for bones and bony structures.At the moment it would appear possible for manufacturers to produces an artifical resin which has no irritational effects and yet has no irritational mechanical strength.
    Notes: Nachdem die Metalle, welche operativ oder aus Zufall in den Körper gelangen und dort verbleiben, in der Möglichkeit ihrer Gewebereizwirkung (Korrosion, Elektrolyse) kurz behandelt wurden, wird auf die Ursache und die Wirkung der Fremdkörperreize eingegangen.Es hat sich in der Praxis bestätigt, daß es Kunstharze gibt, die keine Gewebereize ausüben. Sie müssen physikalisch einen Isolator darstellen, chemisch stabil und mechanisch reizlos sein.Bei der Übernahme statischer Funktionen innerhalb des Körpers treten bei Kunstharzen durch die ihnen eigentümlichen Eigenschaften Schwierigkeiten auf, auf welche näher eingegangen wird.Es zeigt sich, daß die relative junge Kunstharzindustrie noch kein Universalmaterial schaffen konnte, welches in allen Fällen geeignet ist, statisch funktionstüchtig als Knochenersatz verwendet zu werden.Für die Zukunft erscheint es glaubhaft, daß Kunstharze durch die Industrie erstellt werden können, die sowohl reizlos sind, wie auch in ihrer Festigkeit ausreichend sein dürften.
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 458-461 
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    Keywords: Chemistry ; Polymer and Materials Science
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 468-473 
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    Keywords: Chemistry ; Polymer and Materials Science
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 273-280 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Description / Table of Contents: The Corrosion Effects of Varying Concentrations of Nitric and Sulphuric Acids upon Welds on Aluminium and its AlloysThe action of sulphuric and nitric acids upon welded joints on aluminium and various aluminium alloys was examined. Low concentrations of sulphuric acid act first of all on the welded seam of all aluminium materials in use in industry. With higher concentrations, the effect is evenly distributed over the whole surface. Welded aluminium was shown to be highly resistant against concentrations of nitric acid varying between 1 and 65%. In the case of welded aluminium aloys, the welded seam was also the first to be acted on by medium concentrations of sulphuric acid. Welded joints made by the autogenous or the metal-arc processes do not show any great variation in their resistance to corrosion. Annealing or hammering the welds, as well as hammering followed by annealing, has, when made under the conditions obtaining during this examination, no effect upon the resistance to corrosion.
    Notes: Es wurde der Angriff von Schwefel und Salpetersäure auf Schweißverbindungen aus Reinaluminium und Aluminium-Legierungen untersucht. Schwefelsäure greift in den unteren Konzentrationsbereichen bei sämtlichen Aluminium-Werkstoffen bevorzugt die Schweißnähte an, während bei den oberen Konzentrationsgraden eine gleichmäßige Oberflächenabtragung auftritt. - Demgegenüber erwies sich geschweißtes Reinaluminium als praktisch beständig gegen 1 bis 65%ige Salpetersäure. Die geschweißten Aluminium-Legierungen erfuhren besonders bei den mittleren Konzentrationsgraden, durch Salpetersäure ebenfalls einen selektiven Angriff der Schweißnähte.-Die nach dem Autogen- bzw. Metalllichtbogen-Verfahren geschweißten Nähte zeigten keine wesentlichen Unterschiede in ihrer Korrosionsbeständigkeit, obwohl in der Angriffsform gewisse Differenzen bestehen. - Ein Nachglühen oder Hämmern der Schweißraupen sowie ein Hämmern mit anschließender Glühung ist bei den vorliegenden Angriffsbedingungen ohne jeden Einfluß auf das Korrosionsverhalten.
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 310-315 
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    Keywords: Chemistry ; Polymer and Materials Science
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 321-327 
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    Keywords: Chemistry ; Polymer and Materials Science
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 347-347 
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    Keywords: Chemistry ; Polymer and Materials Science
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 327-332 
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    Keywords: Chemistry ; Polymer and Materials Science
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 332-334 
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    Materials and Corrosion/Werkstoffe und Korrosion 4 (1953), S. 336-338 
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    Keywords: Chemistry ; Polymer and Materials Science
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