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  • Polymer and Materials Science  (594)
  • Aerodynamics  (16)
  • Aircraft Propulsion and Power  (9)
  • AERODYNAMICS
  • Animals
  • 1955-1959  (623)
  • 1925-1929
  • 1955  (623)
Collection
Publisher
Years
  • 1955-1959  (623)
  • 1925-1929
Year
  • 1
    Publication Date: 2019-05-23
    Description: An experimental investigation was conducted to determine the performance characteristics an underslung nose-scoop air-induction system for a supersonic airplane. Five different nose shapes, three lip shapes, and two internal diffusers were investigated. Tests were made at Mach numbers from 0 to 1.9, angles of attack from 0 deg to approximately l5 deg, and mass-flow ratios from 0 to maximum obtainable. It was found that the underslung nose-scoop inlet was able to operate at Mach numbers from 0.6 to 1.9 over a large positive angle-of-attack range without adverse effects on the pressure recovery. Although there was no one inlet configuration that was markedly superior over the entire range of operating variables, the arrangement having a nose designed to give increased supersonic compression at low angles of attack, and a sharp lip (configuration designated N3L3) showed the most favorable performance characteristics over the supersonic Mach number range. Inlets with sizable lip radii gave satisfactory performance up to a Mach number of 1.5; however, as a result of an increase in drag, the performance of such inlets was markedly inferior to the sharp-lip configuration above Mach numbers of 1.5. Throughout the range of test Mach numbers all inlet configurations evidenced stable air-flow characteristics over the mass-flow range for normal engine operation. Analysis of the inlet performance on the basis of a propulsive thrust parameter showed that a fixed inlet area could be used for Mach numbers up to 1.5 with only a small sacrifice in performance.
    Keywords: AERODYNAMICS
    Type: NACA-RM-A55G13
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  • 2
    Publication Date: 2019-06-28
    Description: A solution of the equations of the compressible laminar boundary layer including the effects of transpiration cooling is presented. The analysis applies to the flow over an isothermal porous plate with a velocity of fluid injection proportional to the reciprocal of the square root of the distance from the leading edge. The effect of several flow parameters on coolant-flow rates is discussed with the aid of representative examples. A stability analysis indicates that, although transpiration cooling requires a lower surface temperature for stable flow than does internal wall cooling, this lower temperature can be obtained with a smaller expenditure of coolant.
    Keywords: Aerodynamics
    Type: NACA-TN-3404
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  • 3
    Publication Date: 2019-06-28
    Description: The temperature distributions encountered in thin solid wings subjected to aerodynamic heating induce thermal stresses that may effectively reduce the stiffness of the wing. The effects of this reduction in stiffness were investigated experimentally by rapidly heating the edges of a cantilever plate. The midplane thermal stresses imposed by the nonuniform temperature distribution caused the plate to buckle torsionally, increased the deformations of the plate under a constant applied torque, and reduced the frequency of the first two natural modes of vibration. By using small-deflection theory and employing energy methods, the effect of nonuniform heating on the plate stiffness was calculated. The theory predicts the general effects of the thermal stresses, but becomes inadequate as the temperature difference increases and plate deflections become large.
    Keywords: Aerodynamics
    Type: NACA-RM-L55E20c
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  • 4
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    In:  CASI
    Publication Date: 2019-06-28
    Description: Some of the considerations involved in the design of aircraft fuel tanks for liquid hydrogen are discussed herein. Several of the physical properties of metals and thermal insulators in the temperature range from ambient to liquid-hydrogen temperatures are assembled. Calculations based on these properties indicate that it is possible to build a large-size liquid-hydrogen fuel tank which (1) will weigh less then 15 percent of the fuel weight, (2) will have a hydrogen vaporization rate less than 30 percent of the cruise fuel-flow rate, and (3) can be held in a stand-by condition and readied for flight in a short time.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E55F22
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  • 5
    Publication Date: 2019-06-28
    Description: The report summarizes source material on combustion for flight-propulsion engineers. First, several chapters review fundamental processes such as fuel-air mixture preparation, gas flow and mixing, flammability and ignition, flame propagation in both homogenous and heterogenous media, flame stabilization, combustion oscillations, and smoke and carbon formation. The practical significance and the relation of these processes to theory are presented. A second series of chapters describes the observed performance and design problems of engine combustors of the principal types. An attempt is made to interpret performance in terms of the fundamental processes and theories previously reviewed. Third, the design of high-speed combustion systems is discussed. Combustor design principles that can be established from basic considerations and from experience with actual combustors are described. Finally, future requirements for aircraft engine combustion systems are examined.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E54I07
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  • 6
    Publication Date: 2019-05-30
    Description: Aircraft body flare for pitch stability and body flap for pitch control in hypersonic flight
    Keywords: AERODYNAMICS
    Type: NACA-RM-A54J13
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  • 7
    Publication Date: 2019-06-28
    Keywords: AERODYNAMICS
    Type: AGARD-AG-19/P9
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  • 8
    Publication Date: 2019-06-28
    Keywords: AERODYNAMICS
    Type: NACA-TN-3396
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  • 9
    Publication Date: 2019-07-11
    Description: The steady-state over-all performance characteristics of the J65-B3 turbojet engine were determined in an altitude test chamber for four exhaust-nozzle areas at Reynolds number indices of 0.8, 0.4, and 0.2. This range of Reynolds number indices corresponds to a range of altitudes from about sea level to 51,500 feet at a flight Mach number of 0.8. Generalized data are presented to allow calculation of engine performance at any flight condition corresponding to a Reynolds number index within the range investigated. Engine performance calculated from these generalized data is presented for seven altitudes over a range of flight speeds from zero to about 1100 knots. The use of an exhaust nozzle sized to give rated perforce at sea level would permit operation near the point of minimum specific fuel consumption for a wide range of flight conditions and engine speeds.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE55C08
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  • 10
    Publication Date: 2019-07-12
    Description: An investigation was conducted in an altitude test chamber at the NACA Lewis laboratory to determine the effect of a revision of the rated engine operating conditions and modifications to the afterburner fue1 system, flameholder, and shell cooling on the augmented performance of the J71-A-2 (x-29) turbo jet engine operating at altitude . The afterburner modifications were made by the manufacturer to improve the endurance at sea-level, high-pressure conditions and to reduce the afterburner shell temperatures. The engine operating conditions of rated rotational speed and turbine-outlet gas temperature were increased. Data were obtained at conditions simulating flight at a Mach number of 0.9 and at altitudes from 40,000 to 60,000 feet. The afterburner modifications caused a reduction in afterburner combustion efficiency. The increase in rated engine speed and turbine-outlet temperature coupled with the afterburner modifications resulted in the over-all thrust of the engine and afterburner being unchanged at a given afterburner equivalence ratio, while the specific fuel consumption was increased slightly. A moderate shift in the range of equivalence ratios over which the afterburner would operate was encountered, but the maximum operable altitude remained unaltered. The afterburner-shell temperatures were also slightly reduced because of the modifications to the afterburner.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE55D12
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  • 11
    Publication Date: 2019-07-12
    Description: Annular blade-element data obtained primarily from single-stage compressor installations are correlated over a range of inlet Mach numbers and cascade geometry. The correlation curves are presented in such a manner that they are related directly to the low-speed two-dimensional-cascade data of part VI of this series. Thus, the data serve as both an extension and a verification of the two-dimensional-cascade data. In addition, the correlation results are applied to compressor design.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E55G02
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  • 12
    Publication Date: 2019-07-12
    Description: An investigation of the endurance characteristics, at high Mach number, of the J65-W-7 engine was made in an altitude chamber at the Lewis laboratory. The investigation was made to determine whether this engine can be operated at flight conditions of Mach 2 at 35,000-feet altitude (inlet temperature, 250 F) as a limited-service-life engine Failure of the seventh-stage aluminum compressor blades occurred in both engines tested and was attributed to insufficient strength of the blade fastenings at the elevated temperatures. For the conditions of these tests, the results showed that it is reasonable to expect 10 to 15 minutes of satisfactory engine operation before failure. The high temperatures and pressures imposed upon the compressor housing caused no permanent deformation. In general, the performance of the engines tested was only slightly affected by the high ram conditions of this investigation. There was no discernible depreciation of performance with time prior to failure.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE55B07
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  • 13
    Publication Date: 2019-07-12
    Description: During an investigation of the J57-P-1 turbojet engine in the Lewis altitude wind tunnel, effects of inlet-flow distortion on engine stall characteristics and operating limits were determined. In addition to a uniform inlet-flow profile, the inlet-pressure distortions imposed included two radial, two circumferential, and one combined radial-circumferential profile. Data were obtained over a range of compressor speeds at an altitude of 50,000 and a flight Mach number of 0.8; in addition, the high- and low-speed engine operating limits were investigated up to the maximum operable altitude. The effect of changing the compressor bleed position on the stall and operating limits was determined for one of the inlet distortions. The circumferential distortions lowered the compressor stall pressure ratios; this resulted in less fuel-flow margin between steady-state operation and compressor stall. Consequently, the altitude operating Limits with circumferential distortions were reduced compared with the uniform inlet profile. Radial inlet-pressure distortions increased the pressure ratio required for compressor stall over that obtained with uniform inlet flow; this resulted in higher altitude operating limits. Likewise, the stall-limit fuel flows required with the radial inlet-pressure distortions were considerably higher than those obtained with the uniform inlet-pressure profile. A combined radial-circumferential inlet distortion had effects on the engine similar to the circumferential distortion. Bleeding air between the two compressors eliminated the low-speed stall limit and thus permitted higher altitude operation than was possible without compressor bleed.
    Keywords: Aerodynamics
    Type: NACA-RM-SE55E23
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  • 14
    Publication Date: 2019-07-12
    Description: A linear stability analysis and flight-test investigation has been performed on a rolleron-type roll-rate stabilization system for a canard-type missile configuration through a Mach number range from 0.9 to 2.3. This type damper provides roll damping by the action of gyro-actuated uncoupled wing-tip ailerons. A dynamic roll instability predicted by the analysis was confirmed by flight testing and was subsequently eliminated by the introduction of control-surface damping about the rolleron hinge line. The control-surface damping was provided by an orifice-type damper contained within the control surface. Steady-state rolling velocities were at all times less than 1 radian per second between the Mach numbers of 0.9 to 2.3 on the configurations tested. No adverse longitudinal effects were experienced in flight because of the tendency of the free-floating rollerons to couple into the pitching motion at the low angles of attack and disturbance levels investigated herein after the introduction of control-surface damping.
    Keywords: Aerodynamics
    Type: NACA-RM-SL55C22
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  • 15
    Publication Date: 2019-08-14
    Description: Two full-scale models of an inline, cruciform, canard missile configuration having a low-aspect-ratio wing equipped with flap-type controls were flight tested in order to determine the missile's longitudinal aerodynamic characteristics. Stability derivatives and control and drag characteristics are presented for a range of Mach number from 0.7 to 1.8. Nonlinear lift and moment curves were noted for the angle - of-attack range of this test (0 deg to 8 deg). The aerodynamic-center location for angles of attack near 50 remained nearly constant for supersonic speeds at 13.5 percent of the mean aerodynamic chord; whereas for angles of attack near 0 deg, there was a rapid forward movement of the aerodynamic center as the Mach number increased. At a control deflection of 0 deg, the missile's response to the longitudinal control was in an essentially fixed space plane which was not coincident with the pitch plane as a result of the missile rolling. As a consequence, stability characteristics were determined from the resultant of pitch and yaw motions. The damping-in-pitch derivatives for the two angle -of-attack ranges of the test are in close agreement and varied only slightly with Mach number. The horn-balanced trailing-edge flap was effective in producing angle of attack over the Mach number range.
    Keywords: Aerodynamics
    Type: NACA-RM-L54B12
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  • 16
    Publication Date: 2019-08-14
    Description: Two full-scale models of an inline, cruciform, canard missile configuration having a low-aspect-ratio wing equipped with flap-type controls were flight tested in order to determine the missile's longitudinal aerodynamic characteristics. Stability derivatives and control and drag characteristics are presented for a range of Mach number from 0.7 to 1.8. Nonlinear lift and moment curves were noted for the angle-of-attack range of this test (0 deg to 8 deg ). The aerodynamic-center location for angles of attack near 5 deg remained nearly constant for supersonic speeds at 13.5 percent of the mean aerodynamic chord; whereas for angles of attack near O deg, there was a rapid forward movement of the aerodynamic center as the Mach number increased. At a control deflection of O deg, the missile's response to the longitudinal control was in an essentially fixed space plane which was not coincident with the pitch plane as a result of the missile rolling. As a consequence, stability characteristics were determined from the resultant of pitch and yaw motions. The damping-in-pitch derivatives for the two angle-of-attack ranges of the test are in close agreement and varied only slightly with Mach number. The horn-balanced trailing-edge flap was effective in producing angle of attack over the Mach number range.
    Keywords: Aerodynamics
    Type: NACA-RM-L54B12
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  • 17
    Publication Date: 2019-07-11
    Description: An investigation was made of a 1/10-scale dynamically similar model of the Grumman FgF-2 airplane to study its behavior when ditched. The model was landed in calm water at the Langley Tank No. 2 monorail. Various landing attitudes, speeds, and configurations were investigated. The behavior of the model was determined from visual observations, acceleration records, and motion-picture records of the ditchings. Data are presented in tabular form, sequence photographs, time-history acceleration curves, and plots of attitude and speed against distance after contact.
    Keywords: Aerodynamics
    Type: NACA-RM-SL50I29B
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  • 18
    Publication Date: 2019-07-11
    Description: Low-lift drag data are presented herein for one 1/7.5-scale rocket-boosted model and three 1/45.85-scale equivalent-body models of the Grumman F9F-9 airplane, The data were obtained over a Reynolds number range of about 5 x 10(exp 6) to 10 x 10(exp 6) based on wing mean aerodynamic chord for the rocket model and total body length for the equivalent-body models. The rocket-boosted model showed a drag rise of about 0,037 (based on included wing area) between the subsonic level and the peak supersonic drag coefficient at the maximum Mach number of this test. The base drag coefficient measured on this model varied from a value of -0,0015 in the subsonic range to a maximum of about 0.0020 at a Mach number of 1.28, Drag coefficients for the equivalent-body models varied from about 0.125 (based on body maximum area) in the subsonic range to about 0.300 at a Mach number of 1.25. Increasing the total fineness ratio by a small amount raised the drag-rise Mach number slightly.
    Keywords: Aerodynamics
    Type: NACA-RM-SL55D15 , Rept-4987
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  • 19
    Publication Date: 2019-07-11
    Description: A comparison of the zero-lift drag coefficients at Mach numbers from 0.81 to 1.41 of a fin-stabilized parabolic body of revolution as measured in the Langley transonic blowdown tunnel has been made with measurements obtained in free-flight on a larger but geometrically similar model. The absolute values of drag coefficient obtained in the slotted wind tunnel were equivalent to the free-flight drag-coefficient values up to a Mach number of 1.4 when adjustments were made for the effect on viscous drag of differences in Reynolds number between the two test conditions. Excellent agreement was obtained between the two tests for the pressure-drag variation with Mach number, regardless of whether the scale effect on skin friction was considered. Favorable agreement was also obtained between the pressure-drag increments due t o the presence of the stabilizing fins as determined in the wine tunnel from fins-on and fins-off tests and as obtained by a different method in free flight. Tests of a specific airplane configuration to obtain an indication of the problems involved in the construction and tests of small-scale (approximately 7-inch span) complete airplane configuration with internal air flow indicated that reliable zero-lift drag-coefficient measurements at Mach numbers up to 1.4 can be attained with such models, provided the model is constructed with a high but not an unreasonable degree of accuracy.
    Keywords: Aerodynamics
    Type: NACA-RM-L55H09 , Rept-5146
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  • 20
    Publication Date: 2019-07-10
    Description: A free-flight investigation over a Mach number range from 0.6 to 2.0 has been conducted to determine the longitudinal aerodynamic characteristics and effect of rocket jet on zero-lift drag of 1/5-scale models of two ballistic-type missiles, the Hermes A-3A and A-3B. Models of both types of missiles exhibited very nearly linear normal forces and pitching moments over the angle-of-attack range of 8 deg to -4 deg and Mach number range tested. The centers of pressure for both missiles were not appreciably affected by Mach number over the subsonic range; however, between a Mach number of 1.02 and 1.50 the center of pressure for the A-3A model moved forward 0.34 caliber with increasing Mach number. At a trim angle-of-attack of approximately 30 deg, the A-3A model indicated a total drag coefficient 30% higher than the power-off zero-lift drag over the subsonic Mach number range and 10% higher over the supersonic range. Under the conditions of the present test, and excluding the effect of the jet on base drag, there was no indicated effect of the propulsive jet on the total drag of the A-3A model. The propulsive jet operating at a jet pressure ratio p(sub j)/p(sub o) of 0.8 caused approximately 100% increase in base drag over the Mach number range M = 0.6 to 1.0. This increase in base drag amounts to 15% of the total drag. An underexpanded jet operating at jet pressure ratios corresponding approximately to those of the full-scale missile caused a 22% reduction in base drag at M = 1.55 (p(sub j)/p(sub o) = 1.76) but indicated no change at M = 1.30 (p(sub j)/p(sub o) = 1.43). At M = 1.1 and p(sub j)/p(sub o) = 1.55, the jet caused a 50% increase in base drag.
    Keywords: Aerodynamics
    Type: NACA-RM-SL55F15
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  • 21
    Publication Date: 2019-07-11
    Description: An investigation is being conducted in the Langley 20-foot free-spinning tunnel on a 1/24-scale model of the Grumman F11F-1 airplane to determine spin and recovery characteristics and the minimum-size parachute required to satisfactorily terminate the spin in an emergency. Results obtained to date are presented herein. Test results indicate that it may be difficult to obtain an erect or inverted spin on the airplane, but, if a spin is obtained, the spin will be very oscillatory and recovery from the developed erect spin by rudder reversal may not be possible. The lateral controls will have no appreciable effect on recoveries from erect.spins. Recovery from the inverted spin by merely neutralizing the rudder will be satisfactory. After recoveries by rudder reversal and after recoveries from spins without control movement (no spins), the model oftentimes rolled very rapidly about the X-axis. Based on limited preliminary tests made in this investigation to make the model recover satisfactorily, it appears that canards near the nose of the airplane or differentially operated horizontal tails may be utilized to provide rapid recoveries. The parachute test results indicate that an 11-foot-diameter (laid-out-flat) parachute with a drag coefficient of 0.650 (based on the laid- out-flat diameter) and with a towline length equal to the wing span is the minimum-size parachute required to satisfactorily terminate an erect or inverted spin in an emergency.
    Keywords: Aerodynamics
    Type: NACA-RM-SL55G20 , Rept-5121
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  • 22
    Publication Date: 2019-07-11
    Description: An investigation is being conducted in the Langley 20-foot free-spinning tunnel on a l/18 scale model of the Ryan X-13 airplane to determine its spin and recovery characteristics. The spin and recovery characteristics determined to date are presented in this report.
    Keywords: Aerodynamics
    Type: NACA-RM-SL55H08 , Rept-5145
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  • 23
    Publication Date: 2019-07-11
    Description: Tests have been conducted in the Langley 8-foot transonic tunnel on a 0.04956-scale model of the Convair F-102A airplane which employed an indented and extended fuselage, cambered wing leading edges, and deflected wing tips. Force and moment characteristics were obtained for Mach numbers from 0.60 to 1.135 at angles of attack up to 20 . In addition, tests were made over a limited angle-of-attack range to determine the effects of the cambered leading edges, deflected tips, and a nose section with a smooth area distribution. Fuselage modifications employed on the F-102A were responsible for a 25.percent reduction in the minimum drag-coefficient rise between the Mach numbers of 0.85 and 1.075 when compared with that for the earlier versions of the F-102. Although the wing modifications increased the F-102A subsonic minimum drag-coefficient level approximately 0.0020, they produced large decreases in drag at lifting conditions over that for the original (plane-wing) F-102. The F-102A had 15 to 25 percent higher maximum lift-drag ratios than did the original F-102. The F-102A had about 15 percent lower maximum lift-drag ratios at Mach numbers below 0.95 and slightly higher maximum lift-drag ratios at supersonic speeds when compared with those ratios for sn earlier modified-wing version of the F-102. Chordwise wing fences which provided suitable longitudinal stability for the original F-102 were not adequate for the cambered-wing F-102A The pitching-moment curves indicated a region of near neutral stability with possible pitch-up tendencies for the F-102A at high subsonic Mach numbers for lift coefficients between about 0.4 and 0.5.
    Keywords: Aerodynamics
    Type: NACA-RM-SL55D19 , Rept-4990
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  • 24
    Publication Date: 2019-07-12
    Description: A flight test of a rocket-propelled model of the Convair XFY-1 airplane was conducted to determine the lateral stability and control characteristics, The 0.133-scale model had windmilling propellers for this test, which covered a Mach number range of O.70 to 1.12. The center of gravity was located at 13.9 percent of the mean aerodynamic chord. The methods of analysis included both a solution by vector diagrams and simple one- and two-degree-of-freedom methods. The model was both statically and dynamically stable throughout the speed range of the testa The roll damping was good, and the slope of the side-force curve varied little with speed. The rudder was effective throughout the test speed range, although it was reduced to about 43 percent of its subsonic value at supersonic speeds.
    Keywords: Aerodynamics
    Type: NACA-RM-SL55J31
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  • 25
    Publication Date: 2019-08-15
    Description: For a period of ten to fifteen years intensive research and development has been conducted on turbojet propulsion systems for aircraft. During this period much has been learned about the system both from the standpoint of current usage and of future development possibilities. It is the purpose of this report to discuss the current status of the turbojet engine as produced in the United States and to discuss the future possibilities for improvement in the engine and in the fuel. The engine and fuel improvements will be evaluated both from the standpoint of probability of success in obtaining these improvements and from the standpoint of the effects of these improvements on the airplane performance.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-54H23
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  • 26
    Publication Date: 2019-07-12
    Description: The stall-limit line at low speeds was improved somewhat by closing the inlet guide vanes 6 deg, while the design-speed maximum flow and pressure ratio were reduced. The first-stage characteristic curve was moved to lower values of both flog coefficient and equivalent pressure ratio. The second-stage pressure ratio was decreased slightly at high speeds, while the later stages were unaffected.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE55D11
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  • 27
    Publication Date: 2019-07-12
    Description: Available experimental two-dimensional cascade data for conventional compressor blade sections are correlated at a reference incidence angle in the region of minimum loss. Variations of reference incidence angle, total-pressure loss, and deviation angle with cascade geometry, inlet Mach number, and Reynolds number are investigated. From the analysis and the correlations of the available data, rules and relations are evolved for the prediction of blade-profile performance. These relations are developed in simplified forms readily applicable to compressor design procedures.
    Keywords: Aerodynamics
    Type: NACA-RM-E55K01a
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  • 28
    Publication Date: 2019-07-12
    Description: Free-flight tests in the transonic and supersonic speed ranges utilizing rocket-propelled models have been made on two pairs of 1/9-scale Convair YF-102 airplane wings with elevons to investigate the possibility of flutter . These wings had modified 60 deg delta plan forms with the trailing edge swept forward 5 deg. The aspect ratio of two exposed wing panels was 2.19 and the wings had NACA 0004-65 (modified) airfoil sections. The model wings and elevons were dynamic-scale models at sea level of the full-scale wings at 20,000 feet. The first set of wings developed elevon buzz near a Mach number of 1 during both power-on and coasting flight at amplitudes of equal to or greater than +/-4 deg.. The second set of wings did not develop the elevon buzz experienced by the first set but, as the model reached the maximum speed of the test (Mach number 1.93), one or both of the wings suddenly failed, possibly as a result of aerodynamic heating or high stresses imposed on the wings at separation from the booster. No flutter was experienced during either flight.
    Keywords: Aerodynamics
    Type: NACA-RM-SL54L22
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  • 29
    Publication Date: 2019-07-12
    Description: The over-all component performance characteristics of the J71 Type IIA three-stage turbine were experimentally determined over a range of speed and over-all turbine total-pressure ratio at inlet-air conditions af 35 inches of mercury absolute and 700 deg. R. The results are compared with those obtained for the J71 Type IIF turbine, which was previously investigated, the two turbines being designed for the same engine application. Geometrically the two turbines were much alike, having the same variation of annular flow area and the same number of blades for corresponding stator and rotor rows. However, the blade throat areas downstream of the first stator of the IIA turbine were smaller than those of the IIF; and the IIA blade profiles were curve-backed, whereas those of the IIF were straight-backed. The IIA turbine passed the equivalent design weight flow and had a brake internal efficiency of 0.880 at design equivalent speed and work output. A maximum efficiency of 0.896 occurred at 130 percent of design equivalent speed and a pressure ratio of 4.0. The turbine had a wide range of efficient operation. The IIA turbine had slightly higher efficiencies than the IIF turbine at comparable operating conditions. The fact that the IIA turbine obtained the design equivalent weight flow at the design equivalent operating point was probably a result of the decrease in the blading throat areas downstream of the first stator from those of the IIF turbine, which passed 105 percent of design weight flow at the corresponding operating point. The third stator row of blades of the IIA turbine choked at the design equivalent speed and at an over-all pressure ratio of 4.2; the third rotor choked at a pressure ratio of approximately 4.9
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E55A20
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  • 30
    Electronic Resource
    Electronic Resource
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955) 
    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
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  • 31
    Electronic Resource
    Electronic Resource
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 1-1 
    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
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  • 32
    Electronic Resource
    Electronic Resource
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 2-6 
    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: Corrosion Inhibitors in Petroleum Refinery ServiceChemical Inhibitors play a role of increasing importance in the prevention of corrosion in refinery service. After a brief discussion of the theory underlying the effectiveness of corrosion inhibitors, the author reports considerations which must govern the choice of a particular additive for individual application. Progress in the field of anodic, cathodic, and organic inhibitors is reported. Among the former, chromates and nitrites are widely used, especially with waters of low oxygen content. The use of insufficient inhibitors is more harmful than no inhibitor at all, and minimum proper concentration must be carefully determined. Drawbacks of anodic inhibitors exist in hard waters and in the treatment of potable water. In such cases, the purpose is often better served by cathodic inhibitors (e. g. glassy phosphates and calcium bicarbonate). Organic inhibitors are relatively new and open up a vast and promising new field. Special interest attaches to the recent development of sodium benzoate and of organic amines in this service.
    Notes: Chemische Hemmstoffe (Inhibitoren) haben auf dem Gebiete der Korrosionsverhütung in der Erdölraffinerie steigende Bedeutung erlangt. Nach einer kurzen Erörterung der Theorie, die der Wirkung der Hemmstoffe zu Grunde liegt, berichtet der Verfasser über die Gesichtspunkte, die bei der Wahl eines Hemmstoffes im Einzelfalle zu berücksichtigen sind. Es werden die Fortschritte aufgezeigt, die auf dem Gebiete der anodischen kathodischen und organischen Hemmstoffe erzielt wurden. Als anodische Hemmstoffe kommen vorwiegend Chromate und Nitrite zur Anwendung, insbesondere bei Wasser von geringem Sauerstoffgehalt. Dabei ist zu beachten, daß die Anwendung von ungenügenden Mengen Hemmstoff schädlicher ist als überhaupt kein Hemmstoff, weshalb die anzuwendenden Mindestkonzentrationen sorgfältig zu ermitteln sind. Auch besitzen die anodischen Hemmstoffe Nachteile bei Behandlung von hartem Wasser und von Trinkwasser. In solchen Fällen sind kathodische Hemmstoffe, wie glasige Phosphate und Calciumbicarbonat, oft vorzuziehen. Organische Hemmstoffe sind verhältnismäßig neu und eröffnen ein vielseitiges und aussichtsreiches Anwendungsgebiet. Besonderes Interesse verdienen in dieser Hinsicht Natriumbenzoat und organische Amine.
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 9-14 
    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 of Hardware during Storage and ShipmentThe type of corrosion referred to in this article results from failure to remove a11 traces of residual water, pickle, soldering flux, fingerprints, etc., which arise during manufacture. However, in most cases the deciding factor is the quantity of sea water vapour, sulphur oxides or humidity present in the ambient air, as well as the type of material used for packaging. To prevent such corrosion from occuring, packaging materials and containers containing and corrosive agents are used. In most cases, however, protective coatings of mineral oils and greases, usually with an addition of some corrosion inhibitor, are applied. Furthermore, removeable coatings (having a cellulose acetate or butyrate base) are often applied. The articles must be absolutely clean before such coatings can be applied. Finally, the highlights of the pertinent U. S. Government Specifications, which were brought to the lecturer's notice during a recent visit to the U.S.A., are given.
    Notes: Die Ursachen der behandelten Korrosionsart liegen mitunter in Fabrikationsmängeln wie Spülwasser-. Beiz- und Lötmittelrückstanden oder Fingerabdrücken. Meistens sind jedoch der Gehalt der umgebenden Luft an Feuchtigkeit, Schwefeloxyden und Meerwassersprühnebeln oder das Packmaterial entscheidend. Zur Bekämpfung der Korrosion verwendet man Packungen oder Transportbehälter, in denen korrosionsverhütende Verhältnisse bestehen. Meist bringt man jedoch Schutzüberzüge aus Mineralölen oder fetten Ölen auf, die Zusatzmittel, im besonderen Korrosionsinhibitoren, enthalten. Ferner werden abziehbare Überzüge (z. B. auf Celluloseacetat oder -butyralgrundlage) verwendet. Für die Aufbringung der Überzüge müssen die Waren einwandfrei gereinigt sein. Die amerikanischen Spezifikationen für die genannten Schutzverfahren, die der Verfasser bei einer Studienreise näher kennen gelernt hat, werden nach ihren wesentlichen Gesichtspunkten geschildert.
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 15-26 
    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: Solid products of Corrosion as Corrosion-Governing-ElementsCorrosion of metal in aqueous solutions is the result of complicated reactions governed by the electro-chemical properties of the metal and of the electrolytic solution and by the chemical and thermodynamic properties as well as the existing activity and morphological formation of the solid products of corrosion. Exact knowledge of the chemical and physico-chemical properties of the possible solid products of corrosion (oxides, hydroxides, hydroxide-salts) is necessary to understand corrosion in solutions as well as in acid vapours.It is demonstrated by experiments with zinc in sodium chloride solutions how to determine the dispersion and the formation of the products of corrosion by means of microscopes and electronmicroscopes and how to identify these by means of X-ray-photographs and of electron-diffractive spectra. The detailed results show in which way the solid products govern the whole corrosionprocess according to their constitution, formation and dispersal.
    Notes: Der korrosive Angriff eines Metalls in wäßriger Lösung ist das Ergebnis eines komplizierten Zusammenspiels von Faktoren, die durch die elektrochemischen Eigenschaften des Metalls und der Elektrolytlösung bestimmt sind und Faktoren, die gegeben sind durch die chemischen und thermodynamischen Eigenschaften der festen Korrosionsprodukte, sowie deren Reaktionsfähigkeit und morphologische Ausbildung. Voraussetzung für das Verständnis der Korrosionsvorgänge in Lösungen wie in sauren Dämpfen sind genaue Kenntnisse der chemischen und physikalisch-chemischen Eigenschaften der möglichen festen Korrosionsprodukte, Oxyde, Hydroxyde und Hydroxysalze.An einigen Beispielen von Korrosionsversuchen mit Zink in Natriumchloridlösung wird gezeigt, wie mit Hilfe von Mikroskop und Elektronenmikroskop die Verteilung und Ausbildungsform der Korrorionsprodukte festgestellt werden kann und wie diese mit Hilfe von Röntgen- und Elektronenbeugungsaufnahmen identifiziert werden können. Die detaillierten Kenntnisse der Natur der festen Korrosionsprodukte, deren Ausbildungsform und Verteilung lassen erkennen, in welcher Weise diese den ganzen Korrosionsvorgang lenken.
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 33-34 
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    Keywords: Chemistry ; Polymer and Materials Science
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 44-44 
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    Keywords: Chemistry ; Polymer and Materials Science
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 45-45 
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    Keywords: Chemistry ; Polymer and Materials Science
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 52-52 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 52-52 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 53-55 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 55-56 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 81-84 
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    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Description / Table of Contents: The Influence of the Rate of Flowing on the Precipitation of Hardnes and the so Caused Corrosion in Hot-Water-Supply-DevicesPrecipitation of the hardness of waters resulting from metall-dissolution is subject to the alkalinity of the wall. Its rate depends on the composition of the water and on the available concentration of a depolariser; in this way the rate of flowing and of diffusion. It is shown how to eliminate resulting disadvantage by suitable constructions which do not cause lower efficiency of the devices.
    Notes: Die Härteausscheidung aus Wässern als Folge einer Metallauflösung ist abhängig von der Wandalkalität. Die Höhe der Wandalkalität richtet sich nach der Wasserzusammensetzung und der Menge des in der Zeiteinheit zur Verfügung stehenden Depolarisationsmittels, also nach der Diffusionsgeschwindigkeit. Es wird gezeigt, wie durch bauliche Maß nahmen die nachteiligen Faktoren eliminiert werden können, ohne daß die Leistung der Geräte sinkt.
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    Description / Table of Contents: There is a number of particulars basing on laboratory-measurements as well as on practical experiences. They allow a rough choice of material for equipment dealing with sulfuric acid.Formerly all those laboratory-experiments were carried out in static systems of sulfuric acid of different concentrations and temperatures.The data of corrosion obtained in this way do not comply with the requirements of a critical choice of material as in practice the velocity of corrosion is influenced essentially by further numerous varieties.Therefore a laboratory-method to measure corrosion under conditions of different velocities of flowing was developed. Further effects on corrosion, e. g. accumulation of the products of corrosion in the corrosive agent, were investigated too. The measurements on carbon steel and Al-Ni-bronze are discussed in this paper.
    Notes: Man hat eine Anzahl von Daten zur Verfügung, die sowohl auf Laboratoriumsmessungen als auch auf praktischer Erfahrung beruhen und die eine grobe Materialauswahl für eine mit Schwefelsäure arbeitende Apparatur ermöglichen.Was die Laboratoriumsmessungen anbetrifft, so wurden diese früher meistens mit Schwefelsäure verschiedener Konzentration und Temperatur im statischen System durchgeführt. Bekanntlich aber genügen die so ermittelten Korrosionsdaten zu einer kritischen Materialauswahl nicht, da in Wirklichkeit zahlreiche Variablen die Korrosionsgeschwindigkeit wesentlich beeinflussen.In diesem Zusammenhang wurde eine Laboratoriumsmethode entwickelt, die es ermöglicht, Korrosionsmessungen unter verschiedenen Strömungsbedingungen durchzuführen. Auch der Einfluß von anderen Faktoren auf die Korrosion wurde untersucht, z. B. Anhäufen von Korrosionsprodukten in der angreifenden Flüssigkeit.Die Messungen an Kohlenstoffstahl und Aluminium - Nickel - Bronze werden besprochen.
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 72-80 
    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 To-Day State of Phosphatizing on Iron and Non-Ferrous-MetalsPhosphatizing is a electrochemical, cathodically controlled process. The author developed mathematical lawfulness for the formation and decomposition of phosphate-covers which was proved by experiments. The porosity of the covers was determined to be 0.3% of the total surface. Because of their high porosity phosphate-covers are used only in combination of oils, lacquers or varnishes. The methods of phosphatizing are discribed in detail. According to the composition of the phosphatizing bath or the intensity of treatment, thinner or thicker covers are obtained. Thick covers of more than 100 mg/100 cm2 (on nails, screws, etc.) are oiled while thin covers of 25-75 mg/100 cm2 are bottoms for painting.Phosphate-covers do not only serve protection against corrosion but also the decrease of friction of sliding surfaces of machines. These covers of manganese and iron phosphate are applied in combination with lubricants.Phosphatizing is of big importance to the cold-working of iron and steel e. g. to deep-drawing. This method invented by Fr. Singer has been applied in Germany. Later than 1947 it was introduced in Great-Britain and the USA.
    Notes: Der Phosphatierungsprozeß ist ein elektrochemischer, kathodisch gesteuerter Vorgang. Für die Kinetik der Bildung und Zerstörung der Phosphatschichten wurden von w. Machu mathematische Gesetzmäßigkeiten abgeleitet und experimentell bewiesen. Die Porosität der Phosphatschichten wurde zu 0.3% der Gesamtfläche ermittelt. Wegen dieser verhältnismäßig hohen Porosität werden die Phosphatüberzüge nur in Verbindung mit Ölen, Lacken oder Anstrichen verwendet. Die Verfahren der Phosphatierung werden im einzelnen beschrieben.Je nach Zusammensetzung des Phosphatierungsbades oder der Behandlungsintensität erhält man dickere oder dünnere Überzüge. Dicke Schichten von über 100 mg/dm2 für Nägel, Schrauben u. dgl. werden geölt, während die dünnen Schichten von 25-75 mg/dm2 die Grundlage von Anstrichen bilden.Neben dem Korrosionsschutz dienen die Phosphatüberzüge auch zur Verminderung der Reibung von aufeinandergleitenden Maschinenteilen. Diese Schichten aus Mangan- und Eisenphosphaten werden in Verbindung mit Schmiermitteln angewendet.Neben Hilfsmittel bei der Kaltbearbeitung von Eisen und Stahl, z.B. Beim Tiefziehen, ist die Phosphatierung von besonderer Bedeutung. Dieses von Fr. Singer 1935 erfundene und in Deutschland angewendete Verfahren wurde erst nach 1947 in USA und in England eingeführt.
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 94-94 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 97-98 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 100-101 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 99-99 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 149-151 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 136-141 
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    Description / Table of Contents: The Mechanism of the Decomposition of Hydrogen-Peroxide on Metallic LeadThe potentials of the galvanic cells Pb/Pt and Pb/Ag in electrolytes containing 0,01-0,4 mols of H2O2 were plotted against time. The obtained results allow to draw conclusions on the mechanism of the catalytic decomposition of H2O2 on lead.The decomposition of H2O2 on metallic lead in 0,01-0,25 molar solutions of H2O2 at 20, 40 and 60°C temperature is characterized by a period of induction. The effect does not occur at higher concentrations of H2O2. If the specimen is preliminarily dipped into a 0,1 molar solution of H2O2 at 20°C temperature for 30 min. no period of induction occures. The decomposition under these conditions is a reaction of zero order.By the effect of H2O2 on freshly precipitated Pb(OH)2 a number of higher leadoxides are produced. Their general formula is PbOn where n is a number between 2 und 3.Experiments on the influence of the state of the surface on the corrosion of lead are discussed.
    Notes: Der Wasserstoffsuperoxyd-Zerfall auf metallischen Blei wurde elektrochemisch und kinetisch verfolgt, wobei die ständige Änderung der Bleioberfläche durch einige Kontaktsubstanzen, die der 0,01 bis 0,4 mol-H2O2-Lösung zugesetzt wurden, durch Potential-Zeit-Messungen, mittels einer Platin- und Silber-Hilfselektrode verfolgt wurde.Der Wasserstoffsuperoxyd-Zerfall auf metallischem Blei bei 20, 40 und 60°C in 0,01 bis 0,25 mol H2O2-Lösung ist durch eine Induktionsperiode gekennzeichnet, die jedoch bie höheren Konzentrationen vollständig verschwindet. Wird die Bleiprobe vor dem Eintauchen in die H2O2-Versuchslösung in einer 0,1 mol-H2O2-Lösung etwa 30 min bei 20°C behandelt, so verschwindet die Induktionsperiode. Die Zerfallreaktion läuft dann als Reaktion nullter Ordnung ab. Durch Einwirkung von H2O2 auf frisch vorbereitetes Pb(OH)2 entsteht eine Reihe höherer Bleioxyde der allgemeinen Formel PbOn, wo n Werte zwischen 2-3 darstellen kann.
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 152-153 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 154-156 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 157-157 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 158-158 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 162-162 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 205-207 
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    Keywords: Chemistry ; Polymer and Materials Science
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 208-209 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 181-189 
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    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Description / Table of Contents: The Developement of the Cathodic Protection Against Corrosion of Metallic Constructions under Water and in soilsThe first constructions in France beings cathodically protected against corrosion were burried steel-pipe-lines. To-day nearly all the longer and also many short ones in France as well as in North Africa are protected by this method as they are very sensitive to corrosion. Furthermore French engineers have investigated the Protection against corrosion of pipe-line-systems abroad e.g. gas-pipes in the valley of the river po.This method is also used for steel pipe-lines in water like those crossing the river of Seine or those in harbours for the discharging of tankers. In Northern France cathodic protection against corrosion is even allied to important pipe-lines of steel-concrete-make which is of special importance owing to the extra-ordinary aggressiveness of the soils in these districts.Telephone- and power-cables were protected either alone or in connection with steel-pipes. At present cathodic protection is also employed to further constructions like metallic pile-foundations, walls of quays and wharves, sluices in harbours and even ships and floating docks.The different methods to establish the cathodic potential of protection are discusses. Stray-Current-Corrosion of railway-constructions can be prevented by the stray-current itself it the construction to be protected is connected suitably with the tracks. The various types of anodes corresponding to be concerned kinds of soil are discusses. Final considerations deal with the economics of the cathodic protection against corrosion.
    Notes: Die im Erdreich liegenden Rohrleitungen aus Stahl waren die ersten Anlagen, die in Frankreich kathodisch geschützt wurden. Heute werden fast alle längeren und auch sehr viele kurze Stahlrohrleitungen in Frankreich und in Nordafrika auf diese Weise geschützt, da die Leitungen besonders anfällig für Korrosion sind. Außerdem haben französische Ingenieure den Schutz von Rohrleitungsnetzen im Ausland untersucht, z. B. von Gasleitungen in der Po-Ebene.Man wendet diese Schutzart auch auf Stahlrohrleitungen im Wasser an, z. B. für die durch die Seine geführten Leitungen oder für solche Rohrleitungen, wie sie in Häfen für das Entleeren von Tankschiffen diene. Der kathodische Schutz wird in Nordfrankreich auch für bedeutende Rohrleitungen in Stahlbeton angewendet. Dies ist wegen der außer-gewöhnlichen Aggressivität der Böden in diesem Gebiet besonders wichtig.Auch Telephonkabel und elektrische Leitungen für Energieübertragungen wurden entweder für sich oder in Verbindung mit Stahlrohrleitungen geschützt. Der kathodische Schutz wird augenblicklich auch auf andere Anlagen ausgedehnt, beispielsweise auf Fundamente aus Metallpfählen, Kai-Verkleidungen von Häfen und Werften, Schleusen in Häfen und sogar auf Schiffen oder schwimmenden Docks.Es werden die verschiedenen Verfahren zur Erzeugung des kathodischen Schutzpotentials beschrieben. Bei Gefährdung von Bahnlinien durch vagabundierende Ströme kann der Streustrom selbst zum Schutz verwendet werden, wenn man die zu schützende Anlage in geeigneter Weise mit der Schiene verbindet. Die verschiedenen Arten von Anoden, je nach der Bodenbeschaffenheit, werden beschrieben.Abschließende Betrachtungen gelten der Wirtschaftlichen Seite des kathodischen Schutzes.
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 271-272 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 273-274 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 275-275 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 297-300 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. I 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955) 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 325-328 
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    Keywords: Chemistry ; Polymer and Materials Science
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    Description / Table of Contents: Short-time-tests in a new test-chamber for corrosionAt first the author discusses the problems of short time tests and refers to the faults of sprayers operated by spray nozzles. Then he describes the „Aerosol apparatus“ which allows to produce a fine homogenous fog. This device was the basis for the development of a new test chamber for corrosion. Finally the advantages of this device are emphasized and some applied experiments and their results described.
    Notes: Der Verfasser streift zuerst die Probleme, die sich bei Kurzzeitprüfungen stellen und weist auf die Fehler hin, die bei Sprühgeräten auftreten, welche mit Düsen arbeiten. Dann wird ein Aerosolapparat beschrieben, der gestattet, einen feinen und gleichmäßigen Nebel zu erzeugen. Dieses Gerät diente als Grundlage für die Entwicklung einer neuen Korrosionsprüfkammer. Anschließend werden die Vorteile dieser Einrichtung hervorgehoben. Schließlich werden noch praktische Versuche und deren Resultate beschrieben.
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 329-331 
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    Description / Table of Contents: On the resistance to oxidation and Corrosion of ZirconiumGaining an increasing application as oxidizing agent, alloy constituent and material for pipes Zirconium is distinguished like titanium by its high resistance to oxidation and corrosion. On basis of the latest American literature this paper presents a survey of its most important physical properties especially of the influence of deformation and annealing in the manufacturing processes of semifinished products as well as of its thermal and chemical resistance to about 45 different corrosive agents.
    Notes: Zirkonium, das als Oxydationsmittel, Legierungselement und Röhrenbaustoff zunehmende Verwendung findet, zeichnet sich, ähnlich wie Titan, durch hohe Oxydations- und Korrosionsbeständigkeit aus. Die Arbeit gibt an Hand des neueren amerikanischen Schrifttums einen zeitgemäßen Überblick über die wichtigsten physikalischen Eigenschaften von Zirkonium, insbesondere über den Einfluß von Verformung und Glühbehandlung im Verlaufe der Halbzeugfertigung sowie über die thermische und chemische Beständigkeit des Zirkoniums gegen etwa 45 verschiedene angreifende Mittel.
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 343-346 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 352-353 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 362-362 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 366-368 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. III 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 496-501 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 486-495 
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    Description / Table of Contents: The Use of Electric Extensometer Strips in the Testing of MaterialsAs the electric measurement of extension by means of extensometer strips, being a modern as well as convenient method, has proved and become well known to be successfully applicable to all branches of engineering for the investigation of special conditions of wear it was attempted to show the use of this method in solving special problems of material research. Numerous examples prove convincingly that the above described method can be applied profitably even to special problems of the static material testing. The realm of use of the well known little Hartmann und Braun (Frankfurt) extensometer bridge “Pontavi” has been enlarged by a lately developed supplementary apparatus for selective connection of several extensometer strips.
    Notes: Nachdem hinreichend bekannt und unter Beweis gestellt ist daß die „elektrische Dehnungsmessung“ mit Dehnungsmeßstreifen, die ein ebenso modernes wie elegantes Meßverfahren darstellt, auf allen Gebieten der Technik erfolgreich zur Klärung besonderer Beanspruchungsverhältnisse eingesetzt werden kann, wurde versucht, die Nutzanwendung diese Verfahrens bei der Lösung werkstoffkundlicher Sonderaufgaben aufzuzeigen. An zahlreichen Anwendungsbeispielen wird überzeugend gezeigt, daß das eingangs beschriebene Verfahren auch auf den Gebieten der statischen Werkstoffprüfung zur Lösung spezieller Aufgaben nutzbringend Anwendung finden kann. Der Anwendungsbereich der bekannten kleinen Dehnungsmeßbrücke Pontavi der Fa. Hartmann & Braun, Frankfurt wurde durch ein neu entwickeltes Zusatzgerät zum wahlweisen Anschluß mehrerer Dehnungsmeßstreifen in glücklicher Weise erweitert.
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 502-504 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 505-506 
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    Description / Table of Contents: The Corrosion Chemical Behavior of Non-Ferrous Metal upon Alkali Fluoride- and Alkali Hydro Fluorides.1. The Corrosion-Chemical Behavior of Non-Ferrous Metals upon Alkali Fluoride- and Alkali Hydro Fluoride SolutionAs alkali fluoride preservatives protect wooden constructions against fungus growth and insect attack the corrosion chemical behavior of the most important non ferrous metals upon those salts is of as big interest as that of iron which has largely been investigated because of the extensive use of iron in and on wood. Considering that e.g. non ferrous sheet metals for roofing, non ferrous semifinished products armatures and fittings are touching in way impregnated wood resp. that non ferrous metals are applied to iron as protective coating the corrosion chemical behavior of copper, brass, cadmium, tin, zinc, lead and aluminum as well as of aluminum magnesium alloys upon various alkali fluoride and alkali hydro fluoride solutions and upon the solution of an approved commercial product were systematically investigated under various conditions of concentration and temperature according to recommended standards. The obtained results are represented in chartform and discussed amply. The investigated magnesium alloy proved to be to tally resistant under all experimenting conditions while the other metals generally showed a very much differing behavior in different electrolytes.
    Notes: Da Imprägniermittel auf Basis der Alkalifluoride Holzkonstruktionen wirkungsvoll vor Pilzbefall und Insektenfraß schützen, interessiert das korrosions chemische Verhalten der wichtigsten NE-Metalle gegenüber derartigen Salzen etwa in dem gleichen Maße wie das des Eisens, das infolge seiner weitgehenden technischen Verwendung in Holz und an Holz bereits weitgehend geklärt ist. Im Hinblick darauf, daß beispielsweise NE-Metallblech für Dacheindeckungen, NE-Halbzeuge, -Armaturen und -Verbindungselemente mit derart imprägnierten Holzteilen in Berührung kommen bzw. als Schutzüberzug für E-Metalle Verwendung finden, wurde das korrosionschemische Verhalten von Kupfer, Messing, Cadmium, Zinn, Zink, Blei, aluminium sowie das von Aluminium- und Magnesium-Legierungen gegenüber verschiedenen Alkalimono- und Alkalihydrogenfluoridlösungen und gegen Lösungen eines bewährten Handelsproduktes systematisch unter verschiedenen Versuchsbedingungen (Konzentration und Temperatur) in Anlehung an empfohlene Normen untersucht. Die erhaltenen Versuchwerte wurden tabellarisch und schematisch zusammengefaßt und ausführlich diskutiert. Während sich die verschiedenen Metalle in den verschiedenen Elektrolyten im allgemeinen stark unterschiedlich verhielten, ist die untersuchte Mg-Legierung in sämtlichen Versuchslösungen unter allen Versuchsbedingungen vollständig beständig.
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 507-507 
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    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 535-538 
    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 Effect of Light on the Solubility of Copper in electrolytesA survey of the relationship between the photo- and electrochemical reactions in the corrosion of copper is given. On the surface of copper electrodes in a HCl-HNO3-solution photo sensitive covers are formed. If you expose a copper electrode of a certain size, immersed into a 0,1 n KCl solution, to light and keep an other electrode of the same size and in the same solution in darkness a current of about 0,2 mA flows from one electrode to the other. The differences of the solubility of exposed and not exposed copper electodes in 0,1-0,001 n KCl solutions are represented in a diagram. The solubility of the exposed copper electrode is severely inhibited if 1 ccm of a 0,001 m FeSO4 solution is added to the used 0,001 n KCl solution. The sensitivity of ironsalts to visible light causes the formation of a more stable system obeying the equation Fe″ + Cu″ + hv Fe‴ + Cu′.
    Notes: Überblick über den Zusammenhang zwischen photochemischen und elektrochemischen Reaktionen bei der Korrosion des Kupfers. In einer HCl-HNO3-Lösung bilden sich auf der Oberfläche von Kupferelektroden lichtempfindliche Überzüge aus. Setzt man eine Cu-Elektrode von bestimmter Oberfläche in 0,1 n-KCl der Einwirkung einer Lichtquelle aus, während man eine gleichgroße Cu-Elektrode in 0,1 n-KCl in Dunkelheit hält, so fließt zwischen beiden Elektroden ein strom von etwa 0,2 mA. Die zwischen der belichteten und der unbelichteten Cu-Elektrode in 0,1 bid 0,001 n-KCl-Lösung auftretenden Löslichkeitsunterschiede wurden graphisch dargestellt. Nach Zugabe von 1 ml 0,001 m-FeSO4 zu der 0,01 n-KCl ist die Löslichkeit der belichteten Cu-Elektrode verhältnismäßig stark gehemmt, die Lichtempfindlichkeit der Eisensalze gegen sichtbares Licht bewirkt die Bildung eines stabileren Systems, das sich durch die Gleichung Fe″ + Cu″ + hv ⇌ Fe‴ + Cu′ wiedergeben läßt.
    Additional Material: 5 Ill.
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    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 548-549 
    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
    Type of Medium: Electronic Resource
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    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 6 (1955), S. 546-547 
    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
    Type of Medium: Electronic Resource
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