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  • Polymer and Materials Science  (1.521)
  • Aerodynamics  (44)
  • 1990-1994
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  • 1955-1959  (1.565)
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  • 1958  (902)
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  • 1990-1994
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  • 1
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    Preliminary Wind-Tunnel Investigation of the Performance of Republic F-105 Wing-Root Inlet Configurations at Various Angles of Attack and a Mach Number of 2.01 (1957)
    In:  CASI
    Details
    Publikationsdatum: 2019-05-31
    Beschreibung: A 1/13-scale model of the forebody of the Republic F-105 with twin-duct wing-root inlets was tested in the Langley 4- by 4-foot supersonic pressure tunnel through a range of angle of attack from -4 deg to 15 deg at a Mach number of 2.01 and a Reynolds number of approximately 3.4 x 10(exp 6) per foot. The tests were made with four configurations which incorporated varying amounts of sweep and stagger of the inlet leading edges, modifications to the areas of the boundary-layer diverter floor plate, and modifications to the area of the boundary-layer diverter bleed slots. The highest overall pressure recovery at an angle of attack of 0 deg (average total-pressure recovery, 0.84 mass-flow ratio, 0.98) was achieved with configuration having an inlet leading-edge sweep angle of 58 deg with no leading-edge stagger. Stagger was found to improve the angle-of- attack performance, but at a sacrifice in inlet efficiency for an angle of attack of 0 deg. The boundary-layer diverter floor height, of the order of one boundary-layer thickness, was satisfactory for bypassing the fuselage boundary layer. The boundary-layer diverter-plate bleed slots were effective in increasing the total-pressure recovery of the inlet. The total-pressure-recovery contour plots, taken at the compressor-face station, indicate the existence of high-velocity "cores" throughout the inlet operating range.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SL56L12
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  • 2
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    Exploratory Wind-Tunnel Investigation to Determine the Lift Effects of Blowing over Flaps from Nacelles Mounted Above the Wing (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: An exploratory wind-tunnel investigation has been made to determine the lift effects of blowing from nacelles over the upper surface of flaps on a model having a delta wing of aspect ratio 3. Several flap conditions were examined. High-pressure air was blown from an external-pipe arrangement supported above the wing to simulate jet-engine exhaust. The jet momentum- coefficient range was from 0 to 3.0 and the model angle of attack was 0 deg. The results of this limited investigation show that values of jet circulation lift coefficient larger than the Jet reaction were produced with blowing over flaps from nacelles mounted above the wing. 'I!heuse of double slotted flaps with the gap unsealed between the flaps and wing had a large detrimental effect on the lift capabilities. With these gaps sealed, larger lift coefficients were obtained when fantails were added to the nacelles. The longitudinal trim problems created by large diving moments were similar to those encountered with other jet-augmented-flap systems
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TN-4298
    Format: application/pdf
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  • 3
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    Theoretical Calculations of Supersonic Wave Drag at Zero Lift for a Particular Store Arrangement (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: An analysis, based on the linearized thin-airfoil theory for supersonic speeds, of the wave drag at zero lift has been carried out for a simple two-body arrangement consisting of two wedgelike surfaces, each with a rhombic lateral cross section and emanating from a common apex. Such an arrangement could be used as two stores, either embedded within or mounted below a wing, or as auxiliary bodies wherein the upper halves could be used as stores and the lower halves for bomb or missile purposes. The complete range of supersonic Mach numbers has been considered and it was found that by orienting the axes of the bodies relative to each other a given volume may be redistributed in a manner which enables the wave drag to be reduced within the lower supersonic speed range (where the leading edge is substantially subsonic). At the higher Mach numbers, the wave drag is always increased. If, in addition to a constant volume, a given maximum thickness-chord ratio is imposed, then canting the two surfaces results in higher wave drag at all Mach numbers. For purposes of comparison, analogous drag calculations for the case of two parallel winglike bodies with the same cross-sectional shapes as the canted configuration have been included. Consideration is also given to the favorable (dragwise) interference pressures acting on the blunt bases of both arrangements.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TN-4120
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  • 4
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    A study of the motion and aerodynamic heating of missiles entering the earth's atmosphere at high supersonic speeds (1957)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A simplified analysis of the velocity and deceleration history of missiles entering the earth's atmosphere at high supersonic speeds is presented. The results of this motion analysis are employed to indicate means available to the designer for minimizing aerodynamic heating. The heating problem considered involves not only the total heat transferred to a missile by convection, but also the maximum average and local time rates of convective heat transfer.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TN-4047
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  • 5
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    Heat-Transfer Measurements in Free Flight at Mach Numbers up to 14.6 on a Flat-Faced Conical Nose with a Total Angle of 29 Degrees (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Skin-temperature measurements have been made at several locations on a flat-faced cone-cylinder nose which was flight tested on a fivestage rocket-propeller model to a Mach number of 14.64 and a free-stream Reynolds number of 2.0 x 10(exp 6), based on flat-face diameter, at an altitude of 66,300 feet. The copper nose had a 29 deg total-angle conical section which was 1.6 flat-face diameters long. The aerodynamic-heating rates determined from the temperature measurements reached 1,440 Btu/( sec) (sq ft) on the flat face. The heating rates near the center of the flat face agreed well at Mach numbers up to 13.6 with those obtained by a theory for laminar stagnation-point heating in equilibrium dissociated air (Avco Res. Rep. 1). At Mach numbers above 13.6, the heating rates at locations near the center of the flat face became progressively lower than stagnation-point theory and. were 29 percent lower at Mach number 14.6 at the end. of the test. The reason for this behavior of the heating on the central part of the flat face was not determined. Excluding the relatively low heating rates that occurred on the central part of the nose at the highest Mach numbers, the distribution of experimental heating along the innermost 0.79 of the flat-face radius, expressed as a percentage of stagnation-point heating, was in fair agreement with the distribution predicted by laminar theory. At a location of 0.71 radii from the stagnation point, the experimental heating was very near 130 percent of the theoretical stagnation-point rate at Mach numbers from 11 to 14.5. The experimental beating rates on the conical section of the nose were in good agreement with laminar-cone theory using the assumption of theoretical sharp-cone static pressure on the conical section.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L57L03
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  • 6
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    Total-Pressure Distortion and Recovery of Supersonic Nose Inlet with Conical Centerbody in Subsonic Icing Conditions (1957)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Ice was formed on a full-scale unheated supersonic nose inlet in the NACA Lewis icing tunnel to determine its effect on compressor-face total-pressure distortion and recovery.Inlet angle of attack was varied from 0degrees to 12 degrees, free-stream Mach number from 0.17 to 0.28, and compressor-face Mach number from 0.10 to 0.47. Icing-cloud liquid-water content was varied from 0.65 to 1.8 grams per cubic meter at free-stream static air temperatures of 15 degrees and 0 degrees F. The addition of ice to the inlet components increased total-pressure-distortion levels and decreased recovery values compared withclear0air results, the losses increasing with time in ice. The combination of glaze ice, high corrected weight flow, and high angle of attack yielded the highest levels of distortion and lowest values of recovery. The general character of compressor-face distortion with an iced inlet was the same as that for the clean inlet, the total-pressure gradients being predominantly radial, with circumferential gradients occurring at angle of attack. At zero angle of attack, free-stream Mach number of 0.27, and a constant corrected weight flow of 150 pounds per second (compressor-face Mach number of 0.43), compressor-face total-pressure-distortion level increased from about 6 percent in clear air to 12 percent after 21 minutes of heavy glaze icing; concurrently, total-pressure recovery decreased from about 0.98 to 0.945. For the same operating conditions but with the inlet at 12 deg angle of attack, a change in distortion level occurred from about 9 percent in clear air to 14 percent after 2-1/4 minutes of icing, with a decrease in recovery from about 0.97 to 0.94.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-E57G09
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  • 7
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    Approximate Solutions for the Flow About Flat-Top Wing-Body Configurations at High Supersonic Airspeeds (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-05-11
    Beschreibung: The flow about slender flat-top wing-body configurations traveling at high supersonic speeds and small angles of attack is investigated analytically. In the case of conical configurations, approximate algebraic solutions to the flow field are obtained. In the case of configurations which are conical at the vertex but curved in the stream direction, these solutions are combined with a slender-body approximation to the generalized shock-expansion method to obtain the flow downstream of the vertex. Surface pressures were obtained experimentally at Mach numbers from 3.0 to 6.0 and angles of attack up to 6 deg for several flat-top wing-body configurations. These configurations consisted of half-bodies of revolution mounted beneath thin highly swept wings. Three different bodies were employed. The two conical bodies consisted of one-half of a fineness-ratio-5 cone and one-half of a fineness-ratio-2-1/2 cone. The body of the third configuration consisted of one-half of a fineness-ratio-5 ogive. For the ogive configuration, the leading edges of the wing were curved and designed to just maintain the theoretically determined bow shock along the leading edge at a Mach number of 5.0 and an angle of attack of 3 deg. The predictions of the conical flow theory of this paper for the surface pressures are found to be in good agreement with experiment at Mach numbers of 5.0 and 6.0 up to angles of attack of approximately 3 deg. Estimated lift, drag, and pitching-moment coefficients, as well as maximum lift-drag ratio, are also in good agreement with existing experimental data at a Mach number of 5.0 for a conical configuration having an arrow plan-form wing. It is also found that the generalized shock-expansion method yields reasonable good agreement with experiment for the surface pressures on the half-ogive configuration at a Mach number of 5.0 and an angle of attack of 3 deg.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-A58F02
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  • 8
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    Tabulated Data From a Pressure-Distribution Investigation at Mach Number 2.01 of a 45 Deg Sweptback-Wing Airplane Model at Combined Angles of Attack and Sideslip (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-05-11
    Beschreibung: A pressure-distribution investigation of a wing-body combination has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01. The model configuration consisted of an ogive-circular-cylinder body (fineness ratio of approximately ii) and a wing with 45 deg of sweepback at the quarter-chord line, an aspect ratio of 4, and a taper ratio of 0.2. Data were obtained on high-, mid-, and low-wing configurations and for the body and wing alone for a range of angles of attack and yaw from 0 deg to 15 deg. The tabulated pressure coefficients are presented in this report.
    Schlagwort(e): Aerodynamics
    Materialart: NASA-MEMO-10-15-58L
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  • 9
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    Free-Flight Investigation of Aerodynamic Heat Transfer to a Simulated Glide-Rocket Shape at Mach Numbers up to 10 (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-05-11
    Beschreibung: Heat-transfer measurements were made on a simulated glide-rocket shape in free flight at Mach numbers up to 10 and free-stream Reynolds numbers of 2 x 10 based on distance along surface from apex and 3 x 10 based on nominal leading-edge diameter. The model simulated the bottom of a 75 deg delta wing at 8O deg angle of attack. The data indicated that for the test conditions a modified three-dimensional stagnation-point theory will predict to reasonable engineering accuracy the heating on a highly swept wing leading edge, the heating being reduced by sweep by the 3/2 power of the cosine of the sweep angle. The data also indicate that laminar heating rates over the windward surface of a highly swept flat glider wing at moderate angles of attack can be predicted with reasonable engineering accuracy by flat-plate theory using wedge local flow conditions and basing Reynolds numbers on lengths from the wing leading edge parallel to the surface center line.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L58G03
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  • 10
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    Boundary-Layer-Transition Measurements in Full-Scale Flight (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-05-11
    Beschreibung: Chemical sublimation has been employed for boundary-layer-flow visualization on the wings of a supersonic fighter airplane in level flight at speeds near a Mach number of 2.0. The tests have shown that laminar flow can be obtained over extensive areas of the wing with practical wing-surface conditions. In addition to the flow visualization tests, a method of continuously monitoring the conditions of the boundary layer has been applied to flight testing, using heated temperature resistance gages installed in a Fiberglas "glove" installation on one wing. Tests were conducted at speeds from a Mach number of 1.2 to a Mach number of 2.0, at altitudes from 35,000 feet to 56,000 feet. Data obtained at all angles of attack, from near 0 deg to near 10 deg, have shown that the maximum transition Reynolds number on the upper surface of the wing varies from about 2.5 x 10(exp 6) at a Mach number of 1.2 to about 4 x 10(exp 6) at a Mach number of 2.0. On the lower surface, the maximum transition Reynolds number varies from about 2 x 10(exp 6) at a Mach number of 1.2 to about 8 x 10(exp 6) at a Mach number of 2.0.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-H58E28
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  • 11
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    Unsteady Flows in Axial Turbomachines (1957)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Of the various unsteady flows that occur in axial turbomachines certain asymmetric disturbances, of wave length large in comparison with blade spacing, have become understood to a certain extent. These disturbances divide themselves into two categories: self-induced oscillations and force disturbances. A special type of propagating stall appears as a self-induced disturbance; an asymmetric velocity profile introduced at the compressor inlet constitutes a forced disturbance. Both phenomena have been treated from a unified theoretical point of view in which the asymmetric disturbances are linearized and the blade characteristics are assumed quasi-steady. Experimental results are in essential agreement with this theory wherever the limitations of the theory are satisfied. For the self-induced disturbances and the more interesting examples of the forced disturbances, the dominant blade characteristic is the dependence of total pressure loss, rather than the turning angle, upon the local blade inlet angle.
    Schlagwort(e): Aerodynamics
    Materialart: O.N.E.R.A. PAPERS PRESENTED AT THE JOURNEES INTERN. DE SCI. AERON., PT. 2 〈1957〈 (SEE N68-81276) P 1-21
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  • 12
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    Measurement of Static Forces on Internally Carried Bombs of Three Fineness Ratios in Flow Field of a Swept-wing Fighter-bomber Configuration at a Mach Number of 1.61 with Illustrative Drop Path Calculations (1957)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: No abstract available
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L56I18
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  • 13
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    Aerodynamic Research on Fuselages with Rectangular Cross Section (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: The influence of the deflected flow caused by the fuselage (especially by unsymmetrical attitudes) on the lift and the rolling moment due to sideslip has been discussed for infinitely long fuselages with circular and elliptical cross section. The aim of this work is to add rectangular cross sections and, primarily, to give a principle by which one can get practically usable contours through simple conformal mapping. In a few examples, the velocity field in the wing region and the induced flow produced are calculated and are compared with corresponding results from elliptical and strictly rectangular cross sections.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1414 , Jahrbuch 1942 der Deutschen Luftfahrtforschung; 263-279
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  • 14
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    Effects of Body Shape on the Drag of a 45 degree Sweptback-Wing-Body Configuration at Mach Numbers from 0.90 to 1.43 (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: An investigation was made of the effects of body shape on the drag of a 45 deg sweptback-wing-body combination at Mach numbers from 0.90 to 1.43. Both the expansion and compression fields induced by body indentation were swept back as the stream Mach number increased from 0.94. The line of zero pressure change was generally tangent to the Mach lines associated with the local velocities over the wing and body. The strength of the induced pressure fields over the wing were attenuated with spanwise distance and the major effects were limited to the inboard 60 percent of the wing semispan. Asymmetrical body indentation tended to increase the lift on the forward portion of the wing and reduce the lift on the rearward portion. This redistribution of lift had a favorable effect on the wave drag due to lift. Symmetrical body indentation reduced the drag loading near the wing-body juncture at all Mach numbers. The reduction in drag loading increased in spanwise extent as the Mach number increased and the line of zero induced pressure became more nearly aligned with the line of maximum wing thickness. Calculations of the wave drag due to thickness, the wave drag due to lift, and the vortex drag of the basic and symmetrical M = 1.2 body and wing combinations at an angle of attack of 0 deg predicted the effects of indentation within 11 percent of the wing-basic-body drag throughout the Mach number range from 1.0 to 1.43. Calculations of the wave drag due to thickness, the wave drag due to lift, and the vortex drag for the basic, symmetrical M = 1.2, and asymmetrical M = 1.4 body and wing combinations predicted the total pressure drag to within 8 percent of the experimental value at M = 1.43.
    Schlagwort(e): Aerodynamics
    Materialart: NASA-MEMO-10-23-58L
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  • 15
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    Experimental Wind-Tunnel Investigation of the Transonic Damping-in-Pitch Characteristics of Two Wing-Body Combinations (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-17
    Beschreibung: The results of an experimental wind-tunnel investigation of the damping in pitch of two wing-body combinations are presented. The tests were conducted in the Ames 14-foot transonic wind tunnel over a Mach number range from 0.60 to 1.18. Reynolds numbers varied from 2.3 million to 5.5 million. One model with a triangular wing of aspect ratio 2 having NACA 0003-63 sections was oscillated at an amplitude of 1.5 and a frequency of 17 cycles per second. The second model with a straight, tapered wing of aspect ratio 3 having 3-percent biconvex circular-arc sections was oscillated at an amplitude of 1.0 deg and a frequency of 21 cycles per second. The tests were made with the models at a mean angle of attack of 0 deg. The models were oscillated with a dynamic balance that was actuated by an electrohydraulic servo valve. The results of this investigation indicate the usefulness of this new apparatus. The experimental results of a previous damping-in-pitch investigation conducted in the Ames 6- by 6-foot supersonic wind tunnel at Mach numbers from 1.2 to 1.7 are included along with the theoretical results for this Mach number range. In the region of Mach numbers available for comparison, good agreement is shown to exist between the data obtained in the two facilities, except for some inconsistency in the slopes of the curves at M = 1.2 for the triangular wing. The results of this investigation clearly show that for the models tested the maximum values of the damping in pitch occur at Mach numbers very close to 1.0, and that abrupt changes in the pitch damping are encountered near sonic velocity.
    Schlagwort(e): Aerodynamics
    Materialart: NASA-MEMO-11-30-58A
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  • 16
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    An Investigation of the Drag Characteristics of a Tailless Delta-Wing Airplane in Flight, Including Comparison with Wind-Tunnel Data (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-16
    Beschreibung: A series of flight tests were conducted to determine the lift and drag characteristics of an F4D-1 airplane over a Mach number range of 0.80 to 1.10 at an altitude of 40,000 feet. Apparently satisfactory agreement was obtained between the flight data and results from wind-tunnel tests of an 0.055-scale model of the airplane. Further tests show the apparent agreement was a consequence of the altitude at which the first tests were made.
    Schlagwort(e): Aerodynamics
    Materialart: NASA-MEMO-10-8-58A
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  • 17
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    Aerodynamic characteristics at mach numbers from 2.5 to 3.5 of a canard bomber configuration designed for supersonic cruise flight (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-14
    Beschreibung: Resilts have been obtained from an investigation in the Langley Unitary Plan wind tunnel at Mach numbers from 2.5 to 3.5 of a canard-type configuration designed for supersonic cruise flight. Tests extended over an angle-of-attack range from about -4 deg to 11 deg and an angle-of-sideslip range from -4 deg to 6 deg. For the present tests, the results indicate that forebody deflection was an efficient means of providing a sizable positive pitching-moment shift with little or no increase in drag. The test configuration had a trimmed lift-drag ratio of approximately 6.0 at Mach numbers near 3.0 and at a Reynolds number of 2.52 X 10(exp 6). The configuration was both longitudinally and directionally stable. The lift-drag ratios are believed to be somewhat low in as much as the models used for the present tests had large-grain size transition strips fixed to the various surfaces and these strips added wave drag. Also, the model boundary-layer diverter is oversized with respect to a full-scale configuration and therefore contributes additional drag.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L58G16
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  • 18
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    Investigation of the Static Lateral Stability and Aileron Characteristics of a 0.067-Scale Model of the Bell X-2 Airplane at Mach Numbers of 2.29, 2.78, 3.22, and 3.71 (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-13
    Beschreibung: Tests were performed in the high. Mach number test section of the Langley Unitary Plan wind tunnel to determine the static lateral stability. and aileron characteristics of a 0.067-scale model of the Bell X-2 airplane at Mach numbers of 2.29, 2. 78, 3.22, and. 3.71. The results of this investigation indicated that the directional stability of the model was low with directional instability occurring at Mach numbers higher than 3.1 and. angles of attack higher than about 5.0 deg (equivalent lift coefficient of about 0.18). The yaw due to aileron deflection was adverse and, with 10 deg of differential aileron deflection, large enough to overbalance the available directional restoring moment at all angles of attack higher than about 5.0 deg (equivalent lift coefficient of about 0.21) and Mach numbers higher than 2. 5. The model also had positive effective dihedral for all test attitudes and. Mach numbers. A combination of the lateral-stability parameters with the aileron characteristics to form a lateral-stability criterion for a maneuver using ailerons alone indicated that the model has characteristics which would. give unstable aperiodic behavior (divergence) over a large part of the test Mach number and angle-of-attack range.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L57J28a
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  • 19
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    Some Effects of Horizontal-Tail Position on the Vertical-Tail Pressure Distributions of a Complete Model in Sideslip at High Subsonic Speeds (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-15
    Beschreibung: An investigation has been made in the Langley high-speed 7- by 10-foot tunnel of some effects of horizontal-tail position on the vertical-tail pressure distributions of a complete model in sideslip at high subsonic speeds. The wing of the model was swept back 28.82 deg at the quarter-chord line and had an aspect ratio of 3.50, a taper ratio of 0.067, and NACA 65A004 airfoil sections parallel to the model plane of symmetry. Tests were made with the horizontal tail off, on the wing-chord plane extended, and in T-tail arrangements in forward and rearward locations. The test Mach numbers ranged from 0.60 to 0.92, which corresponds to a Reynolds number range from approximately 2.93 x 10(exp 6) to 3.69 x 10(exp 6), based on the wing mean aerodynamic chord. The sideslip angles varied from -3.9 deg to 12.7 deg at several selected angles of attack. The results indicated that, for a given angle of sideslip, increases in angle of attack caused reductions in the vertical-tail loads in the vicinity of the root chord and increases at the midspan and tip locations, with rearward movements in the local chordwise centers of pressure for the midspan locations and forward movements near the tip of the vertical tail. At the higher angles of attack all configurations investigated experienced outboard and rearward shifts in the center of pressure of the total vertical-tail load. Location of the horizontal tail on the wing- chord plane extended produced only small effects on the vertical-tail loads and centers of pressure. Locating the horizontal tail at the tip of the vertical tail in the forward position caused increases in the vertical-tail loads; this configuration, however, experienced considerable reduction in loads with increasing Mach number. Location of the horizontal tail at the tip of the vertical tail in the rearward position produced the largest increases in vertical-tail loads per degree sideslip angle; this configuration experienced the smallest variations of loads with Mach number of any of the configurations investigated.
    Schlagwort(e): Aerodynamics
    Materialart: NASA-MEMO-10-5-58L
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  • 20
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    Basic Pressure Measurements at Transonic Speeds on a Thin 45 deg Sweptback Highly Tapered Wing with Systematic Spanwise Twist Variations (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-15
    Beschreibung: Pressure distributions are presented for a thin highly tapered untwisted 45 deg sweptback wing in combination with a body. These tests were made in the Langley 8-foot transonic pressure tunnel at both 1.0 and 0.5 atmosphere stagnation pressures at Mach numbers from 0.800 to 1.200 through an angle-of-attack range of -4 deg to 12 deg.
    Schlagwort(e): Aerodynamics
    Materialart: NASA-MEMO-10-20-58L
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  • 21
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    Turbulent Skin Friction at High Mach Numbers and Reynolds Numbers (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-10
    Beschreibung: For a number of years now, experimenters have been making measurements of skin friction. Formerly, the main interest was at low Mach numbers; later, measurements were made at supersonic Mach numbers. However, almost all of these measurements were over a limited range of Reynolds numbers. On the other hand, these measurements fairly well determined the effects of Mach number and heat transfer on skin friction. The purpose of this paper is to give the results of skin-friction measurements in turbulent boundary layers at high Mach numbers and high Reynolds numbers where data have not previously existed. The equipment used was expressly designed to provide these conditions. As is well known, it is difficult to obtain high Mach numbers and high Reynolds numbers simultaneously with air in a wind tunnel. In order to avoid condensation, it is necessary to heat the air, with a resulting loss in density and Reynolds number. It is desirable, then, to use a gas that does not condense at high Mach numbers. This suggested helium, which was used as a working fluid in some of the tests. At high Mach numbers in a given wind tunnel, higher Reynolds numbers can be obtained with helium than with air, principally because no heating of the helium is required. The different ratios of specific heats also contribute to the increase. In using helium as a working fluid, it is, of course, necessary to determine the equivalence of air and helium in the turbulent boundary layer.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-A58D28
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  • 22
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    Aerodynamic Characteristics at a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One with Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One with a Flared Afterbody and All-Movable Controls (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-14
    Beschreibung: An investigation has been made to determine the aerodynamic characteristics in pitch at a Mach number of 6.8 of hypersonic missile configurations with cruciform trailing-edge flaps and with all-movable control surfaces. The flaps were tested on a configuration having low-aspect-ratio cruciform fins with an apex angle of 5 degrees; the all-movable controls were mounted at the 46.7-percent body station on a configuration having a 10 degrees flared afterbody. The tests were made through an angle-of-attack range of -2 degrees to 20 degrees at zero sideslip in the Langley 11-inch hypersonic tunnel. The results indicated that the all-movable controls on the flared-afterbody model should be capable of producing much larger values of trim lift and of normal acceleration than the trailing-edge-flap configuration. The flared-afterbody configuration had considerably higher drag than the cruciform-fin model but only slightly lower values of lift-drag ratio.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L58D24
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  • 23
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    NACA Conference on High-speed Aerodynamics. a Compilation of Papers Presented (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-14
    Beschreibung: No abstract available
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-X-67369
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  • 24
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    Aerodynamic Characteristics of a 45 Deg Swept Wing Fighter Airplane Model and Aerodynamic Loads on Adjacent Stores and Missiles at Mach Numbers of 1.57, 1.87, 2.16, and 2.53 (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-14
    Beschreibung: An investigation was performed in the Langley Unitary Plan wind tunnel to determine the aerodynamic characteristics of a model of a 45 deg swept-wing fighter airplane, and to determine the loads on attached stores and detached missiles in the presence of the model. Also included was a determination of aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications on model aerodynamic characteristics. Tests were performed at Mach numbers of 1.57, 1.87, 2.16, and 2.53. The Reynolds numbers for the tests, based on the mean aerodynamic chord of the wing, varied from about 0.9 x 10(exp 6) to 5 x 10(exp 6). The results are presented with minimum analysis.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L58C17
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  • 25
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    Flight Investigation at Low Angles of Attack to Determine the Longitudinal Stability and Control Characteristics of a Cruciform Canard Missile Configuration with a Low-Aspect-Ratio Wing and Blunt Nose at Mach Numbers from 1.2 to 2.1 (1957)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-14
    Beschreibung: A full-scale rocket-powered model of a cruciform canard missile configuration with a low-aspect-ratio wing and blunt nose has been flight tested by the Langley Pilotless Aircraft Research Division. Static and dynamic longitudinal stability and control derivatives of this interdigitated canard-wing missile configuration were determined by using the pulsed-control technique at low angles of attack and for a Mach number range of 1.2 to 2.1. The lift-curve slope showed only small nonlinearities with changes in control deflection or angle of attack but indicated a difference in lift-curve slope of approximately 7 percent for the two control deflections of delta = 3.0 deg and delta = -0.3 deg. The large tail length of the missile tested was effective in producing damping in pitch throughout the Mach number range tested. The aerodynamic-center location was nearly constant with Mach number for the two control deflections but was shown to be less stable with the larger control deflection. The increment of lift produced by the controls was small and positive throughout the Mach number range tested, whereas the pitching moment produced by the controls exhibited a normal trend of reduced effectiveness with increasing Mach number. The effectiveness of the controls in producing angle of attack, lift, and pitching moment was good at all Mach numbers tested.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L55K16
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  • 26
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    Turbulence in the Wake of a Thin Airfoil at Low Speeds (1957)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-13
    Beschreibung: Experiments have been made to determine the nature of turbulence in the wake of a two-dimensional airfoil at low speeds. The experiments were motivated by the need for data which can be used for analysis of the tail-buffeting problem in aircraft design. Turbulent intensity and power spectra of the velocity fluctuations were measured at a Reynolds number of 1.6 x 10(exp 5) for several angles of attack. Total-head measurements were also obtained in an attempt to relate steady and fluctuating wake properties. Mean-square downwash was found to have nearly the same dependence on vertical position in the wake as that shown by total-head loss. For this particular wing, turbulent intensity, integrated across the wake, increased roughly as the 3/2 power of the drag coefficient. Power-spectrum measurements indicated a decrease in frequency as wing angle of attack was increased. The average frequency in the wake was proportional to the ratio of mean wake velocity to wake width.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1427
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  • 27
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    A Theoretical Investigation of the Drag of Generalized Aircraft Configurations in Supersonic Flow (1957)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-13
    Beschreibung: It seems possible that, in supersonic flight, unconventional arrangements of wings and bodies may offer advantages in the form of drag reduction. It is the purpose of this report to consider the methods for determining the pressure drag for such unconventional configurations, and to consider a few of the possibilities for drag reduction in highly idealized aircraft. The idealized aircraft are defined by distributions of lift and volume in three-dimensional space, and Hayes' method of drag evaluation, which is well adapted to such problems, is the fundamental tool employed. Other methods of drag evaluation are considered also wherever they appear to offer amplifications. The basic singularities such as sources, dipoles, lifting elements and volume elements are discussed, and some of the useful inter-relations between these elements are presented. Hayes' method of drag evaluation is derived in detail starting with the general momentum theorem. In going from planar systems to spatial systems certain new problems arise. For example, interference between lift and thickness distributions generally appears, and such effects are used to explain the difference between the non-zero wave drag of Sears-Haack bodies and the zero wave drag of Ferrari's ring wing plus central body. Another new feature of the spatial systems is that optimum configurations generally are not unique, there being an infinite family of lift or thickness distributions producing the same minimum drag. However it is shown that all members of an optimum family produce the same flow field in a certain region external to the singularity distribution. Other results of the study indicate that certain spatial distributions may produce materially less wave drag and vortex drag than comparable planar systems. It is not at all certain that such advantages can be realized in practical aircraft designs, but further investigation seems to be warranted.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1421
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  • 28
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    Aerodynamic Heating and Boundary-Layer Transition on a 1/10-Power Nose Shape in Free Flight at Mach Numbers up to 6.7 and Free-Stream Reynolds Numbers up to 16 x 10(exp 6) (1957)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-13
    Beschreibung: A modified 1/10-power nose shape has been tested in free flight at Mach numbers up to 6.7 and free - stream Reynolds numbers based on diameter up to 16 X 10(exp 6). Measured heating rates were presented and compared with calculated values. Agreement ranges from poor on the forward portion of the nose to good on the rearward portion. The local Reynolds numbers of transition based on calculated momentum thickness varied between 1, 600 and 350. Laminar flow was maintained at momentum thickness Reynolds numbers of about 1,000 until the free-stream Reynolds number based on a length of 1 foot reached about 27 X 10(exp 6). At slightly higher free-stream Reynolds numbers transition occurred at momentum thickness Reynolds numbers as low as 250.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L57E14a
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  • 29
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    Effects of Inlet Modification and Rocket-Rack Extension on the Longitudinal Trim and Low-Lift Drag of the Douglas F5D-1 Airplane as Obtained with a 0.125-Scale Rocket-Boosted Model Between Mach Numbers of 0.81 and 1.64: TED No. NACA AD 399 (1957)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-10
    Beschreibung: A flight investigation was conducted to determine the effects of inlet modification and rocket-rack extension on the longitudinal trim and low-lift drag of the Douglas F5D-1 airplane. The investigation was conducted with a 0.125-scale rocket-boosted model between Mach Numbers of 0.81 and 1.64. This paper presents the changes in trim angle of attack, trim lift coefficient, and low-lift drag caused by the modified inlets alone over a small part of the test Mach number range and by a combination of the modified inlets and extended rocket racks throughout the remainder of the test.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SL57D30
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  • 30
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    Investigation of Drag and Static Longitudinal and Lateral Stability and Control Characteristics of 1/20-Scale Model of McDonnell F4H-1 Airplane at Mach Numbers of 1.57, 1.87, 2.16, and 2.53. Phase II Model (1957)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: Tests were performed in the Langley Unitary Plan wind tunnel to determine the drag and static longitudinal and lateral stability and control characteristics of a 1/20-scale model of the McDonnell F4H-1 airplane at Mach numbers of 1 57, 1 87, 2.16, and 2.53. This is the second phase in a series of tests performed on this model. The Reynolds numbers for these tests, based on the mean aerodynamic chord of the wing, are 1.446 x 10 (exp 6), 1.269 x 10 (exp 6), 1.116 x 10 (exp 6), and 0.714 x 10 (exp 6) at Mach numbers of 1.57, 1.87, 2.16, and 2.53, respectively. The model had a 12 deg. wing tip dihedral, a larger vertical tail, and a modified duct.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-SL7A14
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  • 31
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    Aerodynamic Heating of Blunt Nose Shapes at Mach Numbers up to 14 (1958)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: Results are presented from investigations of the aerodynamic heating rates of blunt nose shapes at Mach numbers up to 14. The wind-tunnel tests examined flat-faced cylinder stagnation-point heating rates over the Mach number range. The tests also examined heat transfer and angle of attack.
    Schlagwort(e): Aerodynamics
    Materialart: L-316
    Format: text
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  • 32
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    Schlieren Movies of the 8-Inch Diameter Rigid Parachute Model of the Cook Research Laboratory Taken During the Fourth Phase of Testing in the Langley Unitary Plan Wind Tunnel (1958)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: Canopy Model IV was tested in four different configuration series. Shroud lines were used in the first three series of tests; none were used in the fourth series. Other variables were Mach number (1.77, 2.17, 2.76), dynamic pressure (290, 250, 155 lb per sq ft), camera speed, and attitude.
    Schlagwort(e): Aerodynamics
    Materialart: L-396
    Format: text
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  • 33
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    On Possible Similarity Solutions for Three-Dimensional Incompressible Laminar Boundary-Layer Flows Over Developable Surfaces and with Proportional Mainstream Velocity Components (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-15
    Beschreibung: Analysis is presented on the possible similarity solutions of the three-dimensional, laminar, incompressible, boundary-layer equations referred to orthogonal, curvilinear coordinate systems. Requirements of the existence of similarity solutions are obtained for the following: flow over developable surface and flow over non-developable surfaces with proportional mainstream velocity components.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-TM-1437
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  • 34
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    Heat-Transfer and Friction Measurements with Variable Properties for Airflow Normal to Finned and Unfinned Tube Banks (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-15
    Beschreibung: A single-line correlation of both the heat-transfer and pressure- drop data for electrically heated unfinned tubes is obtained by evaluating the density in the Reynolds number, specific heat, thermal conductivity, and viscosity at the film temperature, and the density in the friction coefficient at the bulk temperature. The heat-transfer data for finned tubes also exhibit an effect of physical-property variation which is removed by evaluating all properties, including density, at the primary surface temperature, and using k* = 0.015 square root of T/530 for the thermal conductivity of air where T is the absolute temperature. The pressure drop for finned tubes is correlated by the use of bulk density in both the Reynolds number and friction coefficient. The data reported are for Reynolds numbers from 2000 to 35,000, surface temperatures from 600 to 1400 R, and an air inlet temperature of 530 R.
    Schlagwort(e): Aerodynamics
    Materialart: NASA-MEMO-10-9-58E , L-4880
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  • 35
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    Large-Scale Wind-Tunnel Tests of an Airplane Model with an Unswept, Aspect-Ratio-10 Wing, Two Propellers, and Blowing Flaps (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-15
    Beschreibung: An investigation was made to determine the lifting effectiveness and flow requirements of blowing over the trailing-edge flaps and ailerons on a large-scale model of a twin-engine, propeller-driven airplane having a high-aspect-ratio, thick, straight wing. With sufficient blowing jet momentum to prevent flow separation on the flap, the lift increment increased for flap deflections up to 80 deg (the maximum tested). This lift increment also increased with increasing propeller thrust coefficient. The blowing jet momentum coefficient required for attached flow on the flaps was not significantly affected by thrust coefficient, angle of attack, or blowing nozzle height.
    Schlagwort(e): Aerodynamics
    Materialart: NASA-MEMO-12-3-58A
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  • 36
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    Low-Speed Aerodynamic and Hydrodynamic Characteristics of a Proposed Supersonic Multijet Water-Based Hydro-Ski Aircraft with Upward-Rotating Engines (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-15
    Beschreibung: The low-speed aerodynamic and hydrodynamic characteristics of a proposed multijet water-based aircraft configuration for supersonic operation have been investigated. The design features include upward-rotating engines, body indentation, a single hydro-ski, and a wing with an aspect ratio of 3.0, a taper ratio of 0.143, 36.90 sweepback of the quarter-chord line, and NACA 65AO04 airfoil sections. For the aerodynamic investigation, with the flaps retracted, the model was longitudinally and directionally stable up to the stall. The all-movable horizontal tail was capable of trimming the model up to a lift coefficient of approximately 0.87. All flap configurations investigated had a tendency to become longitudinally unstable at stall. The effectiveness of the all-movable horizontal tail increased with increasing lift coefficient for all flap configurations investigated; however, with the large static margin of the configuration with the center of gravity at 0.25 mean aerodynamic chord, the all-movable horizontal tail was not powerful enough to trim all the various flapped configurations investigated throughout the angle-of-attack range. For the hydrodynamic investigation, longitudinal stability during take-offs and landings was satisfactory. Decreasing the area of the hydro-ski 60 percent increased the maximum resistance and emergence speed 40 and 70 percent, respectively. Without the jet exhaust, the resistance was reduced by simulating the vertical-lift component of the forward engines rotated upward. However, the jet exhaust of the forward engines increased the maximum resistance approximately 60 percent. The engine inlets and horizontal tail were free from spray for all loads investigated and for both hydro-ski sizes.
    Schlagwort(e): Aerodynamics
    Materialart: NASA-MEMO-10-13-58L
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  • 37
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    Effect of Nose Length, Fuselage Length, and Nose Fineness Ratio on the Longitudinal Aerodynamic Characteristics of Two Complete Models at High Subsonic Speeds (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-15
    Beschreibung: An investigation has been made of the effects of nose length, fuselage length, and nose fineness ratio on the static longitudinal aerodynamic characteristics of an airplane model with a swept wing and low tail and of a second model with a highly tapered wing of moderate sweep and a T-tail. The tests were conducted in the Langley high-speed 7- by 10-foot tunnel at Mach numbers from 0.60 to 0.92. The nose and body cross sections were circular. For either the model with the swept wing and low tail or the model with the highly tapered wing of moderate sweep and the T-tail, the effects of forebody changes amounted primarily to rotations of the pitching-moment curves (changes in static margin) over the test ranges of angle of attack and Mach number. For the range of body shapes investigated the longitudinal stability at low lift is decreased by an increase in nose length or in fuselage length or by a reduction in nose fineness ratio when the fuselage length is held constant. In general, the stability for all model configurations showed substantially the same variation with changes in forebody area moment. The forebody changes did not alter the angle of attack at which an unstable break occurred in the moment contribution of the T-tail but did alter somewhat the magnitude of the instability.
    Schlagwort(e): Aerodynamics
    Materialart: NASA-MEMO-10-10-58L
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  • 38
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    Free-Spinning-Tunnel Investigation of a 1/17 Scale Model of the Cessna T-37A Airplane (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-15
    Beschreibung: Results of an investigation of a dynamic model in the Langley 20-foot free-spinning tunnel are presented. Erect spin and recovery characteristics were determined for a range of mass distributions and center-of-gravity positions. The effects of lateral displacement of the center of gravity, engine rotation, nose strakes, and increased rudder area were investigated.
    Schlagwort(e): Aerodynamics
    Materialart: NASA-MEMO-3-1-59L , AF-AM-42 , L-237
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  • 39
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    Lift, Drag, and Pitching Moment of an Aspect-Ratio-2 Triangular Wing with Leading-Edge Flaps Designed to Simulate Conical Camber (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-15
    Beschreibung: An investigation was conducted to determine the effectiveness of leading-edge flaps in reducing the drag at lifting conditions of a triangular wing of aspect ratio 2.0. The flaps, deflected to simulate conically cambered wings having a wide range of design lift coefficients, were tested over a Mach number range of 0.70 to 2.22 through an angle-of-attack variation from -6 deg to +18 deg at a constant Reynolds number of 3.68 million based on the wing mean aerodynamic chord. A symmetrical wing of the same plan form and aspect ratio was also tested to provide a basis for comparison. The experimental results showed that with the flaps in the undeflected position, a small amount of fixed leading-edge droop incorporated over the outboard 5 percent of the wing semispan was as effective at high subsonic speeds as conical camber in improving the maximum lift-drag ratio above that of the symmetrical wing. At supersonic speeds, the penalty in minimum drag above that of the symmetrical wing was less than that incurred by conical camber. Deflecting the leading-edge flaps about the hinge line through 80 percent of the wing semispan resulted in further improvements of the drag characteristics at lift coefficients above 0.20 throughout the Mach number range investigated. The lift and pitching-moment characteristics were not significantly affected by the leading-edge flaps.
    Schlagwort(e): Aerodynamics
    Materialart: NASA-MEMO-10-5-58A
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  • 40
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    Preliminary Note on a Correlation of a Boundary-Layer Transition Results on Highly Cooled Blunt Bodies (1957)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: Transition data on highly cooled blunt bodies are correlated in terms of the ratio of wall to local-stream enthalpy, Reynolds number based on displacement thickness, and location of transition. The proposed correlation, although not sensitive enough to predict the exact location of transition does predict the enthalpy ratio below which very early transition on blunt bodies is expected. The correlation is not altered by moderate amounts of surface roughness; however, the location of transition may well be affected by roughness.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-E-57J14
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  • 41
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    Supersonic Wave Interference Affecting Stability (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: Some of the significant interference fields that may affect stability of aircraft at supersonic speeds are briefly summarized. Illustrations and calculations are presented to indicate the importance of interference fields created by wings, bodies, wing-body combinations, jets, and nacelles.
    Schlagwort(e): Aerodynamics
    Materialart: NACA-RM-L55L14a
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  • 42
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    Stability-Derivative Determination from Flight Data (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-26
    Beschreibung: A comprehensive discussion of the various factors affecting the determination of stability and control derivatives from flight data is presented based on the experience of the NASA High-Speed Flight Station. Factors relating to test techniques, determination of mass characteristics, instrumentation, and methods of analysis are discussed. For most longitudinal-stability-derivative analyses simple equations utilizing period and damping have been found to be as satisfactory as more comprehensive methods. The graphical time-vector method has been the basis of lateral-derivative analysis, although simple approximate methods can be useful If applied with caution. Control effectiveness has been generally obtained by relating the peak acceleration to the rapid control input, and consideration must be given to aerodynamic contributions if reasonable accuracy is to be realized.. Because of the many factors involved In the determination of stability derivatives, It is believed that the primary stability and control derivatives are probably accurate to within 10 to 25 percent, depending upon the specific derivative. Static-stability derivatives at low angle of attack show the greatest accuracy.
    Schlagwort(e): Aerodynamics
    Materialart: Flight Test Panel of the Advisory Group for Aeronautical Research and Development Meeting; Oct 20, 1958 - Oct 25, 1958; Copenhagen; Denmark
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  • 43
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    Wind-Tunnel Investigation of Some Effects of Wing Sweep and Horizontal-Tail Height on the Static Stability of an Airplane Model at Transonic Speeds (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-16
    Beschreibung: A research model of an airplane with a configuration suitable for supersonic flight was tested at transonic speeds in order to establish the effects on longitudinal and lateral stability of certain changes in both wing sweep and height of the horizontal tail. Two wings of aspect ratio 3 and taper ratio 0.15, one having the quarter-chord line swept back 30 deg and the other 45 deg, were each tested with the horizontal tail of the model in a low and in a high position. One configuration was also tested with fuselage strakes. The tests were made at Mach numbers from 0.60 to 1.17 and Reynolds numbers from 1.9 x 10(exp 6) to 2.6 x 10(exp 6). The results indicated that a low horizontal-tail position (below the wing-chord plane) gave positive longitudinal stability for the model for all angles of attack used (angles of attack up to 24 deg); whereas, a higher tail position (above the wing-chord plane) resulted in a large reduction in stability at moderate angles of attack. With the higher horizontal tail, the 30 deg-swept-wing model had somewhat more stability than the 45 deg-swept-wing model at subsonic Mach numbers. With the lower tail, the 45 deg-swept-wing model had slightly more stability at all Mach numbers. The model with the 30 deg swept wing had greater directional stability with the tail in the higher rather than the lower position, but the opposite was true for the 45 deg-swept-wing model. The directional stability decreased sharply at high angles of attack; this characteristic was alleviated by the use of fuselage strakes which, however, proved to be detrimental to the longitudinal stability of the model tested.
    Schlagwort(e): Aerodynamics
    Materialart: NASA-MEMO-10-3-58L
    Format: application/pdf
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  • 44
    facet.materialart.
    Unbekannt
    Aerodynamic Characteristics in Sideslip of a Large-Scale 49 deg Sweptback Wing-Body-Tail Configuration with Blowing Applied Over the Flaps and Wing Leading Edge (1958)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-16
    Beschreibung: An investigation has been conducted in the Langley full-scale tunnel to determine the aerodynamic characteristics in sideslip of a large-scale 490 sweptback wing-body-tail configuration having wing leading- edge and flap-blowing boundary-layer control. The wing and tails had an aspect ratio of 3.5, a taper ratio of 0.3, and NACA 65AO06 airfoil sections parallel to the plane of symmetry. The tests were conducted over a range of angles of attack of about -5 deg to 28 deg for sideslip angles of 0 deg, -5.06 deg, -10.15 deg, and -15.18 deg. Lateral and longitudinal stability and control characteristics were obtained for6a minimized blowing rate. The Reynolds number of the tests was 5.2 x 10(exp 6), corresponding to a Mach number of 0.08. The results of the investigation showed that sideslip to angles of about -15 deg did not require, from a consideration of the longitudinal characteristics, blowing rates over the wing leading edge or flap greater than that established as minimum at zero sideslip. The optimum configuration was laterally and directionally stable through the complete lift-coefficient range including the stall; however, maximum lift for sideslip angles greater than about 50 was seriously limited by a deficiency of lateral control. Blowing over the leading edge of the retreating wing in sideslip at a rate greater than that established as minimum at zero sideslip was ineffective in improving the lateral control characteristics. The optimum configuration at zero sideslip had no hysteresis of the aerodynamic parameters upon recovery from stall.
    Schlagwort(e): Aerodynamics
    Materialart: NASA-MEMO-10-11-58L
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 45
    Digitale Medien
    Digitale Medien
    Über die Prüfung und die Korrosion von Weinflaschenkapseln aus dünnverzinntem Blei („Stanniol-Kapseln“) (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 1-6 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Beschreibung / Inhaltsverzeichnis: On the Corrosion of Wine Bottle aps Made of Thinly Tinned Lead (Tinfoil Caps) and their TestingSeveral method have been developed for the testing of the thickness and porosity of the tin layers of the customary tinfoil caps. The tin layers of commercial wine bottles were found to be less than 0,001 mm and for a great part considerably porous.To test the resistance of the caps to corrosion, laboratory experiments and practical storage tests have been carried out with commercially capped bottles. Under certain conditions which might be met in practice the caps were corroded considerably, and in some cases they were deteriorated totally. The corrosion products are lead salts.
    Notizen: Es wurden Verfahren für die Prüfung der Dicke und der Porigkeit der Zinnauflage auf den üblichen sogenannten “Stanniol” - Flaschenkapseln entwickelt. Kapseln von aus dem Handel bezogenen Weinflaschen waren fast stets unter 0,001 mm dick verzinnt und meist erheblich porig.Zur Prüfung der Korrosionsbeständigkeit der Kapseln wurden Laboratoriumsversuche mit Kapseln und praktische Lagerversuche mit handelsüblich verkapselten Flaschen ausgeführt. Unter gewissen Bedingungen, die in der Praxis durchaus vorkommen können, wurden die Kapseln unter Bildung von Bleisalzen erheblich korrodiert, in einigen Fällen sogar völlig zerfressen.
    Zusätzliches Material: 9 Ill.
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080102
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  • 46
    Digitale Medien
    Digitale Medien
    Allgemeines, Theorie und Messung der Korrosion (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 24-26 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080105
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  • 47
    Digitale Medien
    Digitale Medien
    Über das anodische Verhalten von Kupfer-Zink-Legierungen in Natriumcyanidlösungen I (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 17-23 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Beschreibung / Inhaltsverzeichnis: On the Anodic behavior of copper zinc alloys in sodium cyanide solutions IThe solubility of alloyed metal anodes is conditioned by the potential of the most not noble constituent of the alloy and the solubility of te cover primary formed on the surface of this constituent. Zinc and brass could be passivated much more easily tan copper. Both the constituents of the alloy react indepently just loke the pure metals. α + β bras is more active and can not be passivated as easily as α-brass. There are only gradual differences between the corrosion processes as well as between the reactions of anodic solution or passivation. The two metals dissolve one after the other and get passivated iin a process consisting of two steps. The voltage of the alloy shows the existence of a small depolarizing effect of teh metals upon one another.
    Notizen: Die Löslichkeit von Legierungsanoden wird durch das Potential des unedelsten Bestandteiles der Legierung und die Löslichkeit der sich auf diesem Bestandteil primär ausbildenden Deckschicht bestimmt. Zink und Messing ist leichter zu passivieren als Kupfer. Beide Bestandteile reagieren in der Legierung unabhängig voneinander ähnlich wie die reinen Metalle, α + β-Messing ist aktiver und daher schwerer zu passivieren als α-Messing. Zwischen den Korrosionserscheinungen sowie den Vorgängen bei der anodischen Auflösung oder Passivierung der Legierungsanode bestehen nur graduelle Unterschiede. die beiden Metalle geben nacheinander in Lösung und werden in zwei Stufenprozessen passiv. Die Potentiale der Legierung zeigen eine geringe depolarisierende Wirkung der beiden Einzelmetalle aufeinander.
    Zusätzliches Material: 9 Ill.
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080104
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  • 48
    Digitale Medien
    Digitale Medien
    Polyäthylen-Plastikrohre. Lieferarten, Dimensionierung, Eigenschaften, Verlegung und Verbindung (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 69-73 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Beschreibung / Inhaltsverzeichnis: Polythylene plastic pipesPipes of soft and hart polythylene (Supralen soft and supralen hard) are gaining increasing application in constructions for transport of aggressive liquids and gases because of their good properties especially owing to their resistance to corrosion. So this paper presents a general and up to date survey of the commercial types and their dimensions and of the physical (mechanical, thermal, electric, hydraulic, acoustic, optical properties) and corrosion chemical behavior as well as te installation and fitting of polythylene pipes.
    Notizen: Rohre aus Weich- und Hartpolyäthylen (Supralen, weich und Supralen, hart) finden infolge ihrer guten allgemeinen und spezifischen Eigenschaften, insbesondere ihres ausgezeichneten korrosionschemischen Verhaltens, zunehmende Verwendung in Anlagen zur Förderung aggressiver Flüssigkeiten und Gase. Im Hinblick darauf gibt der vorliegende Fortschrittsbericht einen zusammenfassenden und zeitgemäßen Überblick über Lieferarten und Dimensionierung, über das physikalische (mechanische, thermische, elektrische, hydraulische, akustische und optische Eigenschaften) und korrosionschemische Verhalten sowie über die Verlegung und Verbindung von Polyäthylen-Plastikrohren.
    Zusätzliches Material: 6 Ill.
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080204
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  • 49
    Digitale Medien
    Digitale Medien
    Über ein Verfahren zur Kesselsteinbeseitigung (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 74-76 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Beschreibung / Inhaltsverzeichnis: On an method for removal of boiler scaleThe solid incrustations in boilers etc. are removed usually by application of certain acids at those places of the devices where the incrustations have been formed. It is wellknown that the aggressive effect of the acids upon cleaned metal surfaces could be prevented by an addition of certain substances with inhibitive effect which will say that these substances decrease or even prevent acid attacks. The peper contains a report on the inhibitive effect of the „Brindi“-resin and some theoretical conclusions drawn from the experimental results.
    Notizen: Feste Steinbildungen in Kesseln usw. werden in neuerer Zeit bekanntlich da-durch beseitigt, daß sie in den Anlagen, in denen sie sich gebildet haben, durch bestimmte Säuren gelöst wurden. Es ist auch bekannt, daß die aggressive Wirkung der Säuren auf die Metallflächen, die unter den Steinbildungen liegen, wenn letztere aufgelöst sind, dadurch verhütet wird, daß der Säure bestimmte Stoffe zugesetzt werden, die als Inhibitoren wirken, d. h. den Säureangriff verringern oder u. U. ganz verhüten. Im vorliegenden Aufsatz ist die diesbezügliche Wirkung des „Brindiharzes“ als Inhibitor laboratoriumstechnisch festgestellt und versucht worden, aus den Ergebnissen einige theoretische Folgerungen zu ziehen.
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080205
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  • 50
    Digitale Medien
    Digitale Medien
    Nichtmetallische anorganische Werkstoffe (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 96-97 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080209
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  • 51
    Digitale Medien
    Digitale Medien
    Organische Werkstoffe (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 98-99 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080210
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  • 52
    Digitale Medien
    Digitale Medien
    Überzüge organischer Natur (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 104-106 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080213
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  • 53
    Digitale Medien
    Digitale Medien
    „Über die Wärmeleitfähigkeit von Stählen bei hohen Temperaturen“. Nr. 263. Von H. Lange und R. Kohlhaas. 1. Teil: Literaturbericht. Westdeutscher Verlag, Köln. 1956. 48 S., 26 Abb. u. 8 Tab. DM 10,70 (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 114-114 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080217
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  • 54
    Digitale Medien
    Digitale Medien
    Metallurgical Thermochemistry, 2. Auflage. London, Pergamon Press 1956. O. Kubaschewski und E. LL. Evans. Bd. 1 der International Series of Monographs in Metal Physics and Physical Metallurgy (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 115-116 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080222
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  • 55
    Digitale Medien
    Digitale Medien
    Les Aciers Fins & Spéciaux Français. Revue Trimestrielle. La Chambre Syndical Des Producteurs D'Aciers Fins et Spéciaux, Paris, Nr. 22, 137 Seiten, März 1956, Preis 350 Frs. (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 116-116 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080226
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  • 56
    Digitale Medien
    Digitale Medien
    ASTM standards on copper and copper alloys. ASTM Committee B-5, on Copper Alloys, Cast and Wrought, Copper and Copper Alloys, Cast and Wrought, Copper and Copper-Alloy Electrical Conductors, Non-Ferrous Metals Used in Copper Alloys. American Society for Testing Materials, Philadelphia. 1956. XIV, 642 S. $ 5,75 (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 116-116 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080229
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  • 57
    Digitale Medien
    Digitale Medien
    Tagungsbericht (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 121-122 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Zusätzliches Material: 2 Ill.
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080234
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  • 58
    Digitale Medien
    Digitale Medien
    Anorganische Überzüge nichtmetallischer Natur (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 299-301 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080513
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  • 59
    Digitale Medien
    Digitale Medien
    Überzüge organischer Natur (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 302-305 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080514
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  • 60
    Digitale Medien
    Digitale Medien
    Der Lizenzvertrag und die internationale Patentverwertung von E. Neuberg. Verlag Chemie, GmbH., Weinheim/Bergstr. 1956. 3. erweit. Auflage. 144 S. Ganzleinen DM 6,90 (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 313-313 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080517
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  • 61
    Digitale Medien
    Digitale Medien
    Tagungsberichte (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 315-315 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080523
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  • 62
    Digitale Medien
    Digitale Medien
    Kurzreferate zu den Originalarbeiten (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. X 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080526
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  • 63
    Digitale Medien
    Digitale Medien
    Werden die Bleifarben im Rostschutz „entbehrlich“?? (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 345-345 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Beschreibung / Inhaltsverzeichnis: Will lead colors become dispensable?Minium is a theoreically ideal protective pigment whose application may be entrusted without any danger even to little trained personnel. Protective covers are formed in the minimum film which prevent underrusting. Its electrochemical effect upon the metallic surface is independent of the chemical properties of the binder. Iron wash primers free from lead may be applied only under certain conditons. New directions confirm that lead colors are indispensable.
    Notizen: Die Bleimennige ist ein „theoretisch ideales“ Schutzpigment, dessen anwendung man völlig gefahrlos auch weniger geschulten Hilfskräften überlassen kann.  -  In ihrem Film bilden sich Schutzschichten, die die Unterrostung verhindern.  -  Ihre elektrochemische Einwirkung auf den metallischen Untergrund ist von der chemischen Natur des Bindemittels unabhängig.  -  Bleifreie Eisengrundiermittel sind nur bedingt anwendbar.  -  Neue Betriebsvorschriften bestätigen die Unentbehrlichkeit der Bleifarben.
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080605
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  • 64
    Digitale Medien
    Digitale Medien
    Nichtmetallische anorganische Werkstoffe (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 357-360 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080609
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  • 65
    Digitale Medien
    Digitale Medien
    Überzüge organischer Natur (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 369-370 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080613
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  • 66
    Digitale Medien
    Digitale Medien
    Metallische überzüge (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 99-101 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080211
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  • 67
    Digitale Medien
    Digitale Medien
    Magnesium - Fabricating and Casting. OEEC, Paris, 1956, 78 S., 19 Abb. DM 5,- (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 114-114 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080215
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  • 68
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    Digitale Medien
    Modernes Schleifen und Polieren. Von W. Burkart 2. wesentlich erweiterte, völlig neu bearbeitete Aufl. des 1954 erschienenen Buches „neuzeitliche Schleif- und Polierpraxis“. E. G. Leuze, Saulgau/Wttbg. 1956. 280 S., 170 Abb., 11 Zeichn. u. 8 Tab. Kunstledereinband. DM 16,40 (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 114-114 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080219
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  • 69
    Digitale Medien
    Digitale Medien
    Korrosion und Verschleiß von Stählen und ihre Bekämpfung in Dampferzeugungsanlagen sowie im Maschinen- und Fahrzeugbau. Von G. W. Akimow. Übers. v. Frahn. Verlag Technik, Berlin, 1956. 179 S., 100 Abb. u. 35 Taf. Geb. DM 18,20 (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 116-116 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080223
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  • 70
    Digitale Medien
    Digitale Medien
    Werkstoff-Ratgeber. Von H. v. Rauhut. W. Girardet, Essen, 1956. 514 S., 23 Abb. Leinen. DM 34,80 (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 116-116 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080227
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  • 71
    Digitale Medien
    Digitale Medien
    Monographie „50 Jahre Braunkohle“ (1902/1955) von W. Schwahn. Verl. Die Braunkohle, Düsseldorf 1956. 134 S., DM 9,- (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 117-117 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080231
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  • 72
    Digitale Medien
    Digitale Medien
    Nachrichten (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 122-123 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080235
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  • 73
    Digitale Medien
    Digitale Medien
    Das Vanalverfahren - Ein neuartiger Korrosionsschutz (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 125-131 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Beschreibung / Inhaltsverzeichnis: The Vanal Process A new Way to Protection against CorrosionThe Paper contains a description of a new method to protect the surface of fireproof building-materials against untimely corrosion at high temperatures. The protective effect depends on surface tension. So this principle has been applied to protection against corrosion for the first time. Suitably arranged protective covers prevent any penetration of gases and slags. The technological and economical advantages of this process especially by application of silicon carbide are explained by means of practical examples.
    Notizen: Es wird ein neues Verfahren beschrieben, durch das die Oberflächen feuerfester Baustoffe vor vorzeitiger Korrosion bei hohen Temperaturen geschützt werden. Die Wirkung beruht auf dem Gesetz der Oberflächenspannung, das hierfür erstmalig angewandt wird. Durch entsprechend ausgerichtete Schutzschichten wird das Eindringen von Gasen und Schlacken verhindert. An Hand von Beispielen as der Praxis wird der technische und wirtschaftliche Vorteil dieses Verfahrens besonders bei Siliciumcarbid erläutert.
    Zusätzliches Material: 10 Ill.
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080302
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  • 74
    Digitale Medien
    Digitale Medien
    Anorganische Überzüge nichtmetallischer Natur (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 170-170 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080311
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  • 75
    Digitale Medien
    Digitale Medien
    Metallische Überzüge (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 240-240 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080409
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  • 76
    Digitale Medien
    Digitale Medien
    Patentschau (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 244-244 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080412
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  • 77
    Digitale Medien
    Digitale Medien
    Nachrichten (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 448-448 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080727
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  • 78
    Digitale Medien
    Digitale Medien
    Die Korrosion in Hochtemperaturkesseln (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 587-596 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Beschreibung / Inhaltsverzeichnis: Corrosion in High-Temperature-BoilersExperiences with corrosion of highly heat resisting steels in high temperature boilers in Germany are discussed by means of the working 600° boilers after 40 000 h of operation. Steam scalling in pure steam is very low. As soon as steam will be solid noticeably corrosive attacks will become dangerous. According to the high standard to water treatment such effects could be prevented so that damages caused by the water must be considered unusual.Damages caused by smoke occured as soon as the flying ashes contained alkali sulfates. The area of damage will be there where a eutectic mixture of sulfates could melt. There are some measures how to prevent this corrosion.Steels containing vanadium may not be used above 600°C as vanadium scaling might occur which was learnt in burning oils containing vanadium.
    Notizen: Die Erfahrungen über das Korrosionsverhalten der hochwarmfesten Stähle in Hochtemperaturkesseln werden in Deutschland an Hand der im Betriebe befindliche 600°-Kessel nach rd. 40 000-stündiger Betriebszeit besprochen. Die Dampfzunderung in reinem Dampf ist gering. Gefahren treten erst auf, sobald der Dampf merkbar verunreinigt ist. dieses läß sich bei dem heutigen hohen Stande der Wasseraufbereitung vermeiden, so daß Korrosionsschäden von der Wasserseite her als ungewöhnlich zu betrachten sind.Schäden von der Rauchgasseite her sind bekannt geworden, sobald in der Flugasche Alkalisulfate vorkommen. Der Schadensbereich liegt in erster Linie dort, wo ein Eutektikum der Sulfate zu schmelzen vermag. Es werden Wege angegeben, wie diese Korrosion zu vermeiden ist.Vanadinhaltige Stäle scheiden für Temperaturen oberhalb 600° aus, da dann dieselbe Vanadinzunderung auftreten kann, welche von der Verfeuerung vanadinhaltiger Öle her bekannt ist.
    Zusätzliches Material: 17 Ill.
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570081005
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  • 79
    Digitale Medien
    Digitale Medien
    Eisenmetalle (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 610-614 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570081009
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  • 80
    Digitale Medien
    Digitale Medien
    Metallische Überzüge (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 629-631 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570081013
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  • 81
    Digitale Medien
    Digitale Medien
    Organische Werkstoffe (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 622-628 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570081012
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  • 82
    Digitale Medien
    Digitale Medien
    Nichtmetallische anorganische Werkstoffe (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 291-293 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080510
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  • 83
    Digitale Medien
    Digitale Medien
    Organische Werkstoffe (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 294-296 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080511
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  • 84
    Digitale Medien
    Digitale Medien
    Metallische Überzüge (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 297-298 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080512
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  • 85
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    Digitale Medien
    Forschungsberichte d. Wirtschafts- u. Verkehrsministeriums Nordrhein-Westfalen. Heft 311 u. 312. Westdeutsch. Verl., Köln 1956/57 (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 313-313 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080516
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  • 86
    Digitale Medien
    Digitale Medien
    Jahrbuch der Oberflächentechnik. 13. Auflage. Hrsg. W. Wiederholt. Berlin, Metall-Verlag 1957. 1130 S., 159 Abb., 42 Taf., 63 Tab. Geb. DM 19,50 (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 314-314 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080520
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  • 87
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    Digitale Medien
    Grundlagen der Wissenschaft und Technologie des Kautschuks. Von J. Le Bras, übers. v. D. Schmidt. Berliner Union, Stuttgart 1956. 390 S., 212 Abb., 47 Tab. Leinen DM 36,- (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 314-315 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080522
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  • 88
    Digitale Medien
    Digitale Medien
    Polyvinylchlorid-Plastikrohre. Lieferarten, Dimensionen, Eigenschaften, Prüfung, Bearbeitung, Verbindung und Verlegung (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 324-329 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Beschreibung / Inhaltsverzeichnis: Polyvinylchloride Plastik PipesPipes of polyvinylchloride (Supradur) are gaining increasing application in contructions for transport of aggressive liquids and gases because of their good properties especially owing to their resistance to corrosion. So this paper presents a general and up to date survey of the commercial types and their dimensions and of the physical and corrosion chemical behavior as well as the methods of installation and fitting of polyvinylchloride pipes.
    Notizen: Rohre aus Polyvinylchlorid (Supradur) finden infolge ihrer guten allgemeinen und spezifischen Eigenschaften, insbesondere ihres ausgezeichneten Korrosionschemischen Verhaltens, zunehmende Verwendung in Anlagen zur Förderung aggressiver Flüssigkeiten und Gase. Im Hinblick darauf gibt der vorliegende Fortschrittsbericht einen zusammenfassenden und zeitgemäßen Überblick über Lieferarten und Dimensionierung, über das physikalische und korrosionschemische Verhalten sowie über die Verlegung und Verbindung von Polyvinylchlorid-Plastikrohren.
    Zusätzliches Material: 12 Ill.
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080603
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  • 89
    Digitale Medien
    Digitale Medien
    Eisenmetalle (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 349-352 
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    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080607
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  • 90
    Digitale Medien
    Digitale Medien
    Graphische Darstellung der Konzeption von Lokalelementen (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 385-389 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Beschreibung / Inhaltsverzeichnis: Graphical representation of the theory of local cellsThe article is concerned with a graphical representation of the theory of local cells by means of the experimentally realized relation \documentclass{article}\pagestyle{empty}\begin{document}$$ e_1 - e_0 = i\frac{{{\rm W}_{\rm a} \cdot {\rm W}_{\rm k}}}{{{\rm W}_{\rm a} + {\rm W}_{\rm k}}} $$\end{document} respectively by a corresponding relation regarding the influences of alterations of polarization. e1 is the total voltage of the electrode bearing the local cell. The voltages of the local cell are cA and cK and its current is i. eo is the total voltage of the electrode at i = 0. Wa and Wk are the coefficients of resistance of the anodic and cathodic locations. Fig. 1. The diagram containing all the partial terms necessary to describe the properties of local cells results from the numerical relations between the constant terms c and W. Fig. 2. The author shows that you will be unable to construct the diagram on basis of the relation above mentioned only. In special cases only some of the partial terms mentioned are available. For the terms c and W depending on current density the diagram is given by curves resulting from a great number of experimental data.
    Notizen: Der vorliegende Artikel verfolgt die graphische Darstellung der Konzeption von Lokalelementen auf Grund der experimentell zugänglichen Beziehung \documentclass{article}\pagestyle{empty}\begin{document}$$ e_1 - e_0 = i\frac{{{\rm W}_{\rm a} \cdot {\rm W}_{\rm k}}}{{{\rm W}_{\rm a} + {\rm W}_{\rm k}}} $$\end{document} bzw. einer entsprechenden Beziehung, in welcher Rücksicht genommen wurde auf die Polarisationsänderungen der Potentiale und Widerstände. ei ist das Gesamtpotential der Elektrode mit dem Lokalelement, dessen Potentiale εa und εk sind, bei einem Stromdurchgang i, eo ist das Gesamtpotential derselben Elektrode bei i = 0. Wa bzw. Wk sind die Widerstands-werte an der anodischen bzw. kathodischen Stelle (s. Abb. 1). Aus den rechnerischen Beziehungen, die für konstante Werte ε und W gelten, folgt das Diagramm, in welchem man alle Teilgrößen, die in der Konzeption der Lokalelemente vorkommen, wiederfinden kann (s. Abb. 2). Es wird darauf aufmerksam gemacht, daß die obenerwähnte Beziehung nicht zur Konstruktion dieses Diagramms genügt. Man muß jedoch zu diesem Diagramm kommen, wenn man für denselben Zweck in Sonderfällen einige der erwähnten Teilgrößen kennt. Bei den Größen ε und W, die stromabhängig sind, ist das entsprechende Diagramm durch Kurven gegeben, zu denen man eine gehörige Zahl Versuchsangaben kennen muß.
    Zusätzliches Material: 2 Ill.
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080702
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  • 91
    Digitale Medien
    Digitale Medien
    Eisenmetalle (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 410-414 
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    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080707
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  • 92
    Digitale Medien
    Digitale Medien
    Metallische Überzüge (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 430-430 
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    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080711
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  • 93
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    Digitale Medien
    Copper smelting and refining in the USA. Technical Assistance Mission's Report. Organisation for European Economic Co-operation. Paris 1954, 74 S. Preis: ffr. 200, -  (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 444-444 
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    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080715
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  • 94
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    Digitale Medien
    Logarithmische rechentafeln. Von F. W. Küster. 68.-73. Aufl. Hrsg. v. A. Thielu. K. Fischbeck. W. de Gruyter, Berlin 1956. XV., 302 S. Geb. Preis:DM 1680 (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 444-444 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080719
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  • 95
    Digitale Medien
    Digitale Medien
    Passivierende Filme und Deckschichten. Anlaufschichten, Mechanismus ihrer Entstehung und ihrer Schutzwirkung gegen Korrosion. Vorträge, gehalten anläßlich der Diskussionstagung des Korrosionsausschusses der Deutschen Gesellschaft für Metallkunde am 13. u. 14. Okt. 1955 in Frankfurt/M. Hrsg. H. Fischer, K. Hauffeu. W. Wiederholt. Springer, Berlin 1956. 400 S., 169 Abb. Geb. Preis: DM 43,50 (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 445-445 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080722
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  • 96
    Digitale Medien
    Digitale Medien
    Kurzreferate zu den Originalarbeiten (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. XVI 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570080728
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  • 97
    Digitale Medien
    Digitale Medien
    Über den Einfluß von Spurenelementen auf die Zunderbeständigkeit hitzebeständiger Legierungen (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 574-579 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Beschreibung / Inhaltsverzeichnis: On the Influence of Trace Elements on the Non Scaling Properties of High Temperature Resistent AlloysThe alloys which are employed at heat transport materials are noted out by more or less high contents of trace elements of which calcium and cerium are the most important ones. These additives cause a considerable improvement of the resistance to oxidation. The results of high temperature oxidation experiments of allosy with and without those quality improving additives are reported. The author shows that the effectivity of those elements is caused by an increased adhesiveness of the oxide layer which is formed during the high temperature glowing.The results of x-ray-photographic and spermicroscopic investigations on the problem of the formation of the oxide layers on ion-chrome-aluminium-alloys are published.
    Notizen: Metallegierungen, die als Heizleiterwerkstoffe Verwendung finden, zeichnen sich durch einen mehr oder weniger hohen Gehalt an gewissen Spurenelementen aus, unter denen Calcium und Cer die bedeutendste Rolle spielen. Diese Zusätze bedingen eine erhebliche Verbesserung der Oxydationsbeständigkeit der Heizleiterlegierungen. Es wird über experimentelle Ergebnisse der Hochtemperatuorxydation solcher Legierungen mit und ohne qualitätserhöhende Zusätze berichtet und nachgweisen, daß der Effekt jener Elemente in der Verbesserung der Haftfestigkeit der sich während der Hochtemperaturglühung ausbildenden Oxydschicht zu suchen ist.Zur Frage der Oxydausbildung auf Eisen-Chrom-Aluminium-Legierungen werden röntgenographische und elektronenmikroskopische Ergebnisse mitgeteilt.
    Zusätzliches Material: 4 Ill.
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570081003
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  • 98
    Digitale Medien
    Digitale Medien
    Neue Wege des Korrosionsschutzes von Eisen in Böden (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 596-602 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Beschreibung / Inhaltsverzeichnis: New Methods of Iron Protection in SoilsThe conditions of formation of the active and passiv behavior of iron are given. The structure of the soil resp. the alteration of the capillar and noncapillar porosity play a decisive role. Then the factors like solid water, soil air, soil resistance and acidity which influence the corrosion processes in soils are discussed. The ratio soil water to soil air was found to be characterizing the corrosion of iron in soils. Every soil has a specific aggressivity which is determined by the water capacity of the soil.The authors gives further advices how to decrease the corrosion of iron in soils with and without cathodic protection, by addition of inhibitors and by preparing artificial airation cells.
    Notizen: In der vorliegenden Arbeit werden zuerst die Bedingungen für das Zustandekommen eines aktiven bzw. passiven Verhaltens des Eisens gegeben, wobei Bodenstruktur bzw. Änderungen der kapillaren und nichtkapillaren Porosität des Bodens eine entscheidende Rolle spielen. Anschließend werden die die im Boden ablaufenden Korrosionsprozesse beeinflussenden Faktoren diskutiert, and zwar Bodenwasser, Bodenluft, Bodenwiderstand und Wasserstoffionen-Konzentration. Dabei wurde das Verhältnis, „Bodenwasser zu zu Bodenluft“ als maßgebender, die Eisenkorrison im Erdboden regulierender Faktor, gefunden. Jeder Boden besitzt eine spezifisches Aggressivität, die durch das Annahmevermögen des Bodens an Wasser bestimmt ist.In der Arbeit werden weiter Ratschläge für der Verminderung der Eisenkorrosion im Erdreich ohne und mit kathodischem Korrosionsschutz, durch Zusatz chemischer Hemmstoffe und durch Erzeugung eines künstlichen Belüftungselementes gegeben.
    Zusätzliches Material: 4 Ill.
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570081006
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  • 99
    Digitale Medien
    Digitale Medien
    Gummi als Korrosionsschutz (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 603-606 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Beschreibung / Inhaltsverzeichnis: Rubber for Protection against CorrosionA survey of the mechanic and chemical properties of protective materials, especially rubber vulcanizates, is followed by a description of the working and testing methods which explains the special requirements of DIN 28051 and 28055 to operating and designing engineers.Furthermore the properties of rubber plated pipes are compared with those of massive plastic pipes. Before the chemical behavior of protective rubber coverings is discussed in general the behavior of protective paints is treated. The applicability of synthetic elastomers could not be discussed in detail. As mentioned in the first part of the artidle they may not be judged on their chemical behavior only. Then the latest development of those plastic materials is commented which will show better resistance to oxidizing agents. They are interesting products of the oldest hard rubber manufactury which has been producing plastics for mroe than 50 years and which together with a French manufactory has been leading in development and introduction of hard an soft rubber coating since 1885.
    Notizen: Nach einem Überblick über die mechanischen und chemischen Voraussetzungen von Korrosionsschutzmaterialien, insbesondere Kautschukvulkanisaten, werden Arbeits- und Prüfverfahren geschildert, die dem Betriebsmann und Konstrukteur von Apparatebauteilen die besonderen Anforderungen der DIN 28051 und 28055 erläutern.Ferner werden die Eigenschaften gummiplattierter Rohrleitungen denen von Massivrohrleitungen auf Kunststoffbasis gegenübergestellt. Bevor auf das allgemeine chemische erhalten von Schutzgummierungen eingegangen wird, wird das Verhalten von Anstrichen als Korrosionsschutz behandelt. Ohne im Detail auf die Einsatzmöglichkeiten synthetischer Elastomere, die, wie im ersten Tel des Aufsatzes hervorgehoben wird, keineswegs lediglich aus deren chemischen Verhalten beurteilt werden dürfen, einzugehen, werden kurz neuere Entwicklungen von Kunststoffen gestreift, die geeignet zu sein scheinen, die bestehende Lücke gegen stark oxydierende Medien zu schließen. Es sind besonders interessante Erzeugnisse des ältesten europäischen Hartgummi-Werkes, das seit über fünf Jahrzehnten auch andere Kunststoffe herstellt und das neben einer französischen Firma maßgeblich an der Einführung und Entwicklung der Hart- und Weichgummierungen seit 1885 beteiligt ist.
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570081007
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  • 100
    Digitale Medien
    Digitale Medien
    Überzüge organischer Natur (1957)
    Weinheim [u.a.] : Wiley-Blackwell
    Materials and Corrosion/Werkstoffe und Korrosion 8 (1957), S. 634-640 
    Details
    ISSN: 0947-5117
    Schlagwort(e): Chemistry ; Polymer and Materials Science
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Maschinenbau
    Materialart: Digitale Medien
    URL: http://dx.doi.org/10.1002/maco.19570081015
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