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  • Polymer and Materials Science  (3,775)
  • Life and Medical Sciences  (673)
  • AERODYNAMICS  (98)
  • Aircraft Design, Testing and Performance  (85)
  • 1955-1959  (4,631)
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  • 1
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    In:  CASI
    Publication Date: 2006-10-26
    Keywords: AERODYNAMICS
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  • 2
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    In:  CASI
    Publication Date: 2006-10-26
    Keywords: AERODYNAMICS
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  • 3
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    In:  CASI
    Publication Date: 2006-10-26
    Keywords: AERODYNAMICS
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  • 4
    Publication Date: 2006-03-16
    Keywords: AERODYNAMICS
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  • 5
    Publication Date: 2012-05-11
    Keywords: AERODYNAMICS
    Type: RM-2419-NASA , RM-2419-NASA
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  • 6
    Publication Date: 2019-05-11
    Description: A flight investigation was made of the lift and drag of a sweptwing fighter airplane in the basic configuration and in a slats-locked-closed configuration over a Mach number range from about 0.63 to about 1.44. At a nominal lift coefficient of 0.1 negligible drag-coefficient difference existed between the two configurations over a comparable Mach number and altitude range. For the basic configuration at zero lift the supersonic drag level was about three times as great as the subsonic drag level, which was about 0.01, whereas the drag-due-to-lift factor increased about 137 percent over the test Mach number range. At comparable Mach numbers the high-altitude data produced a larger lift-curve slope and showed a more pronounced variation of lift-curve slope in the transonic region than did the low-altitude data. For the high-altitude data the lift-curve slope at a Mach number of 1.44 was approximately 62 percent of the value at a Mach number of 0.9.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-10-1-58H , AFRC-E-DAA-TN47945
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  • 7
    Publication Date: 2019-05-23
    Description: Wind tunnel data of X-15 and B-52 aircraft models carry loads and mutual interference
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-184
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  • 8
    Publication Date: 2019-05-23
    Description: Wind tunnel tests - effect of wind induced loads on dynamically scaled model of large missile in launching position
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-109
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  • 9
    Publication Date: 2019-05-23
    Description: High subsonic speed of static longitudinal aerodynamic characteristics of delta wing configuration for angle of attack from 0 deg to 90 deg
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-168
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  • 10
    Publication Date: 2019-05-23
    Description: Stability and control of variable sweep wing configuration with outboard wing panels swept back 75 degrees at Mach 2.01
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-32
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  • 11
    Publication Date: 2019-05-23
    Description: Zero angle of attack performance of isentropic spike inlet designed for maximum external compression at hypersonic speed
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-4
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  • 12
    Publication Date: 2019-05-29
    Description: Transonic wind tunnel study of aerodynamic characteristics of blunt reentry vehicles at varying angles of attack
    Keywords: AERODYNAMICS
    Type: NASA-MEMO-1-21-59L
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  • 13
    Publication Date: 2019-05-30
    Description: Hypersonic flutter tests on rectangular flat-plate models and double-wedge airfoils in helium flow
    Keywords: AERODYNAMICS
    Type: NASA-MEMO-4-8-59L
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  • 14
    Publication Date: 2019-05-23
    Description: Wind tunnel studies at supersonic and transonic speeds to determine aerodynamic characteristics of variable sweep wing aircraft - configuration
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-206
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  • 15
    Publication Date: 2019-05-23
    Description: Mach number and air temperature effect on hypersonic flow over blunt bodies
    Keywords: AERODYNAMICS
    Type: NASA-MEMO-10-9-58A
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  • 16
    Publication Date: 2019-05-23
    Description: Overall stage and stator blade element performance with straight stator and tilted stator in transonic axial flow compressor stage
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-99
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  • 17
    Publication Date: 2019-05-23
    Description: Pressure measurements in flight over conically cambered delta wing of F-102A aircraft at transonic speeds
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-48
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  • 18
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    In:  Other Sources
    Publication Date: 2019-05-10
    Keywords: AERODYNAMICS
    Type: NASA-CR-50493 , RM-2417-NASA
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  • 19
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    In:  Other Sources
    Publication Date: 2019-05-10
    Keywords: AERODYNAMICS
    Type: JPL-170
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  • 20
    Publication Date: 2019-05-29
    Description: Low speed measurements of oscillatory lateral stability derivatives of 60 degree delta wing bomber model
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-13
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  • 21
    Publication Date: 2019-05-30
    Description: Pitch and control stiffness effects on flutter characteristics of all-moveable wing and vertical and horizontal tails on fighter aircraft at supersonic speeds
    Keywords: AERODYNAMICS
    Type: NASA-MEMO-10-16-58L
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  • 22
    Publication Date: 2019-05-30
    Description: Aerodynamic effects of airfoil thickness on transonic flutter characteristics of swept and unswept wings
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-79
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  • 23
    Publication Date: 2019-05-23
    Description: Effect of forebody strakes on aerodynamic characteristics in sideslip and pitch of hypersonic aircraft configurations
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-116
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  • 24
    Publication Date: 2019-05-23
    Description: Determination of loads due to wing twist at transonic and low supersonic speeds
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-126
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  • 25
    Publication Date: 2019-05-23
    Description: Investigation of amplitude and phase shift of static pressure variations in supersonic diffuser for separate oscillation of spike and bypass
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-10
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  • 26
    Publication Date: 2019-05-23
    Description: Fighter aircraft external stores ejection at transonic and supersonic speeds
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-128
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  • 27
    Publication Date: 2019-05-23
    Description: Aerodynamic characteristics of variable sweep aircraft configurations - low altitude supersonic vehicle
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-142
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  • 28
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-89
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  • 29
    Publication Date: 2019-06-27
    Description: Constant chord, trailing edge, control deflection effects on aerodynamic loading characteristics of 60 degree delta wing-body combination at transonic speeds
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-122
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  • 30
    Publication Date: 2019-06-27
    Description: Wind tunnel determination of supersonic flow properties in vicinity swept, delta, and trapezoidal wing-body combinations
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-64
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  • 31
    Publication Date: 2019-06-27
    Description: Full-scale wind tunnel determination of effect of corrugated canister surface on static aerodynamic characteristics of reentry capsule
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-220
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  • 32
    Publication Date: 2019-06-27
    Description: Pressure distribution on hypersonic glide configuration having 79.5 deg sweepback and 45 deg dihedral at Mach number of 4.95
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-223
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  • 33
    Publication Date: 2019-07-13
    Description: Turbojet engine reliability has long been an intense interest to the military users of this type of aircraft propulsion. With the recent inauguration of commercial jet transport this subject has assumed a new dimension of importance. In January l96 the Lewis Research Center of the NASA (then the MACA) published the results of an extensive study on the factors that affect the opera- center dot tional reliability of turbojet engines (ref. 1). At that time the report was classified Confidential. In July l98 this report was declassified. It is thus appropriate at this time to present some of the highlights of the studies described in the NASA report. In no way is it intended to outline the complete contents of the report; rather it is hoped to direct attention to it among those who are center dot directly concerned with this problem. Since the publication of our study over three years ago, the NASA has completed a number of additional investigations that bear significantly on this center dot subject. A second object of this paper, therefore, is to summarize the results of these recent studies and to interpret their significance in relation to turbojet operational reliability.
    Keywords: Aircraft Design, Testing and Performance
    Type: SAE National Aeronautic Meeting; Mar 31, 1959 - Apr 03, 1959; New York, NY; United States
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  • 34
    Publication Date: 2019-08-17
    Description: An investigation of the low-subsonic stability and control characteristics of a model of a flat-bottom hypersonic boost-glide configuration having 78 deg sweep of the leading edge has been made in the Langley full-scale tunnel. The model was flown over an angle-of-attack range from 10 to 35 deg. Static and dynamic force tests were made in the Langley free-flight tunnel. The investigation showed that the longitudinal stability and control characteristics were generally satisfactory with neutral or positive static longitudinal stability. The addition of artificial pitch damping resulted in satisfactory longitudinal characteristics being obtained with large amounts of static instability. The most rearward center-of-gravity position for which sustained flights could be made either with or without pitch damper corresponded to the calculated maneuver point. The lateral stability and control characteristics were satisfactory up to about 15 deg angle of attack. The damping of the Dutch roll oscillation decreased with increasing angle of attack; the oscillation was about neutrally stable at 20 deg angle of attack and unstable at angles of attack of about 25 deg and above. Artificial damping in roll greatly improved the lateral characteristics and resulted in flights being made up to 35 deg angle of attack.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-X-201 , L-452
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  • 35
    Publication Date: 2019-08-17
    Description: Acceleration, airspeed, and altitude data obtained with an NACA VGH recorder from a four-engine commercial transport airplane operating over a northwestern United States-Alaska route were evaluated to determine the magnitude and frequency of occurrence of gust and maneuver accelerations., operating airspeeds, and gust velocities. The results obtained were then compared with the results previously reported in NACA Technical Note 3475 for two similar airplanes operating over transcontinental routes in the United States. No large variations in the gust experience for the three operations were noted. The results indicate that the gust-load experience of the present operation closely approximated that of the central transcontinental route in the United States with which it is compared and showed differences of about 4 to 1 when compared with that of the southern transcontinental route in the United States. In general, accelerations due to gusts occurred much more frequently than those due to operational maneuvers. At a measured normal-acceleration increment of 0.5g, accelerations due to gusts occurred roughly 35 times more frequently than those due to operational maneuvers.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-1-17-59L
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  • 36
    Publication Date: 2019-08-17
    Description: An analysis is made of wing deflection and streamwise twist measurements in rough-air flight of a large flexible swept-wing bomber. Random-process techniques are employed in analyzing the data in order to describe the magnitude and characteristics of the wing deflection and twist responses to rough air. Power spectra and frequency-response functions for the wing deflection and twist responses at several spanwise stations are presented. The frequency-response functions describe direct and absolute response characteristics to turbulence and provide a convenient basis for assessing analytic calculation techniques. The wing deformations in rough air are compared with the expected deformations for quasi-static loadings of the same magnitude, and the amplifications are determined. The results obtained indicate that generally the deflections are amplified by a small amount, while the streamwise twists are amplified by factors of the order of 2.0. The magnitudes of both the deflection velocities and the twist angles are shown to have significant effects on the local angles of attack at the various stations and provide the main source of aerodynamic loading, particularly at frequencies in the vicinity of the first wing-vibration mode.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-12-3-58L
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  • 37
    Publication Date: 2019-08-17
    Description: Analysis of the vortex model proposed by Kriebel, Seidel, and Schwind shows this representation of rotating stall satisfies, at least approximately, the requirements at the cascade. Cascade-parameter-variation effects on rotating stall were studied in a circular cascade and single-stage compressor. Modification of the single-stage compressor stopped the rotating-stall pattern and permitted observation of the pressure and velocity distribution around the annulus. Closer observation might be possible with proper flow-visualization techniques, such as a water pump.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-3-16-59W
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  • 38
    Publication Date: 2019-08-17
    Description: In an attempt to find an aerodynamic means of counteracting the transonic trim change of a fighter airplane, lower surface spoilers were tested on a 0.055-scale wind-tunnel model. The Mach number range of the tests was 0.8 to 1.2 at Reynolds numbers of approximately 4 million. Although the spoilers produced a moderate decrease in the trim change at low altitudes, they also produced a large increase in drag. Pressure-distribution tests with external fuel tanks showed large pressure changes on the lower surface of the wing due to the tanks.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-12-27-58A
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  • 39
    Publication Date: 2019-08-17
    Description: The Levy method which deals with an idealized structure was used to obtain the natural modes and frequencies of a large-scale built-up 45 deg. delta wing. The results from this approach, both with and without the effects of transverse shear, were compared with the results obtained experimentally and also with those calculated by the Stein-Sanders method. From these comparisons it was concluded that the method as proposed by Levy gives excellent results for thin-skin delta wings, provided that corrections are made for the effect of transverse shear.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-2-2-59L , L-153
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  • 40
    Publication Date: 2019-08-17
    Description: A cambered and twisted triangular wing of aspect ratio 2 in combination with a cambered body was investigated experimentally to determine the effectiveness of the camber in reducing the drag due to lift at trim at supersonic speeds. Four arrangements were tested comprising all combinations of a symmetrical and a cambered wing with a symmetrical and a cambered body. The camber shape investigated was derived by linearized lifting surface theory for triangular wings with sonic leading edges and satisfied the requirement that the wing be trimmed at the design Mach number and lift coefficient. The experimental results for the cambered wing and cambered body showed that the drag coefficient at trim was always greater, at the same lift coefficient, than that for the untrimmed symmetrical wing and body. The trim lift coefficient was positive and decreased with increasing Mach number. At the design Mach number of 2.24, the trim lift coefficient was somewhat lower and the drag coefficient was higher than values predicted by linearized lifting surface theory for the wing alone. A comparison of the trim lift-drag ratio of the cambered wing and cambered body with values obtained by trimming the symmetrical wing and symmetrical body either with a canard or a trailing-edge flap showed that, at approximately the design Mach number the cambered configuration developed a somewhat higher value than the trailing-edge flap configuration but a lower value than the canard configuration.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-2-3-59A
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  • 41
    Publication Date: 2019-08-17
    Description: The maximum Mach number and altitude capabilities of the Bell X-2 research airplane were achieved during a program conducted by the U.S. Air Force with Bell Aircraft Corp. providing operational support and the National Aeronautics and Space Administration providing instrumentation and advisory engineering assistance. A maximum geometric altitude of 126,200 feet was attained at a static pressure of 9.4 pounds per square foot and a dynamic pressure of 19.1 pounds per square foot. During the last flight of the airplane, a maximum Mach number of 3.20 was reached. The directionally divergent maneuver which terminated the final high Mach number flight was precipitated by the loss in directional stability that resulted from increasing the angle of attack. The yawing moment from the lateral control was sufficient to initiate the divergence and also to cause,, indirectly, rolling moments that were greater than the aileron capabilities of the airplane. The ensuing violent motions-resulting from inertial roll coupling caused the loss of the aircraft.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-X-137
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  • 42
    Publication Date: 2019-08-16
    Description: The first flight of the North American X-15 research airplane was made on June 8, 1959. This was accomplished after completion of a series of captive flights with the X-15 attached to the B-52 carrier airplane to demonstrate the aerodynamic and systems compatibility of the X-15//B-52 combination and the X-15 subsystem operation. This flight was planned as a glide flight so that the pilot need not be concerned with the propulsion system. Discussions of the launch, low-speed maneuvering, and landing characteristics are presented, and the results are compared with predictions from preflight studies. The launch characteristics were generally satisfactory, and the X-15 vertical tail adequately cleared the B-52 wing cutout. The actual landing pattern and landing characteristics compared favorably with predictions, and the recommended landing technique of lowering the flaps and landing gear at a low altitude appears to be a satisfactory method of landing the X-15 airplane. There was a quantitative correlation between flight-measured and predicted lift-drag-ratio characteristics in the clean configuration and a qualitative correlation in the landing configuration. A longitudinal-controllability problem, which became severe in the landing configuration, was evident throughout the flight and, apparently, was aggravated by the sensitivity of the side-located control stick. In the low-to-moderate angle-of-attack range covered, the longitudinal and directional stability were indicated to be adequate.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-X-195
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  • 43
    Publication Date: 2019-08-16
    Description: A study has been made of the subsonic pressure distributions and loadings for a 45 deg sweptback-wing and body combination at angles of attack up to 36 deg. The wing had an aspect ratio of 5.5, a taper ratio of 0.53, and NACA 64A010 sections normal to the quarter-chord line and was mounted on a slender body of fineness ratio 12.5. Test results are presented for Mach numbers of 0.30 and 0.50 with corresponding Reynolds numbers of 1.5 and 2.0 million, respectively. The stall patterns and spanwise loadings at high angles of attack for the present model are correlated with those for other 45 deg sweptback wing and body combinations having aspect ratios between 4.0 and 8.0. A tentative approach is presented for extrapolating the Weissinger span-loading method to higher angles of attack, and for deriving the spanwise-load distributions for 45 deg sweptback wings at angles of attack above 20 deg. The investigation also included tests of the body in combination with only one panel of the swept wing. The problem of estimating the normal-force coefficient for the single panel at high angles of attack is considered.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-1-18-59A
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  • 44
    Publication Date: 2019-08-16
    Description: Results of a cyclic load test made by NASA on an EB-47E airplane are given. The test reported on is for one of three B-47 airplanes in a test program set up by the U. S. Air Force to evaluate the effect of wing structural reinforcements on fatigue life. As a result of crack development in the upper fuselage longerons of the other two airplanes in the program, a longeron and fuselage skin modification was incorporated early in the test. Fuselage strain-gage measurements made before and after the longeron modification and wing strain-gage measurements made only after wing reinforcement are summarized. The history of crack development and repair is given in detail. Testing was terminated one sequence short of the planned end of the program with the occurrence of a major crack in the lower right wing skin.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-3-15-59L , AF-AM-171
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  • 45
    Publication Date: 2019-08-16
    Description: Flight tests were made to determine the capability of positioning a gliding airplane for a landing on a 5,000-foot runway with special reference to the gliding flight of a satellite vehicle of fixed configuration upon reentry into the earth's atmosphere. The lift-drag ratio and speed of the airplane in the glides were varied through as large a range as possible. The results showed a marked tendency to undershoot the runway when the lift-drag ratios were below certain values, depending upon the speed in the glide. A straight line dividing the successful approaches from the undershoots could be drawn through a lift-drag ratio of about 3 at 100 knots and through a lift-drag ratio of about 7 at 185 knots. Provision of a drag device would be very beneficial, particularly in reducing the tendency toward undershooting at the higher speeds.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-3-12-59L , L-406
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  • 46
    Publication Date: 2019-08-16
    Description: Several approximate procedures for calculating the bending-moment response of flexible airplanes to continuous isotropic turbulence are presented and evaluated. The modal methods (the mode-displacement and force-summation methods) and a matrix method (segmented-wing method) are considered. These approximate procedures are applied to a simplified airplane for which an exact solution to the equation of motion can be obtained. The simplified airplane consists of a uniform beam with a concentrated fuselage mass at the center. Airplane motions are limited to vertical rigid-body translation and symmetrical wing bending deflections. Output power spectra of wing bending moments based on the exact transfer-function solutions are used as a basis for the evaluation of the approximate methods. It is shown that the force-summation and the matrix methods give satisfactory accuracy and that the mode-displacement method gives unsatisfactory accuracy.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-2-18-59L , L-143
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  • 47
    Publication Date: 2019-08-15
    Description: The Bell D-188A VTOL airplane is a horizontal-attitude VTOL fighter with tilting engine nacelles at the tips of a low-aspect-ratio unswept wing and additional engines in the fuselage. The model could be flown smoothly in hovering and transition flight. In forward flight the model could be flown smoothly at the lower angles of attack but experienced an uncontrollable directional divergence at angles of attack above about 16 deg.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-3-16-59L , TED-AD-3147 , L-241
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  • 48
    Publication Date: 2019-08-15
    Description: Flapwise bending moments were calculated for a teetering rotor blade using a reasonably rapid theoretical method in which airloads obtained from wind-tunnel tests were employed. The calculated moments agreed reasonably well with those measured with strain gages under the same test conditions. The range of the tests included one hovering and two forward-flight conditions. The rotor speed for the test was very near blade resonance, and difficult-to-calculate resonance effects apparently were responsible for the largest differences between the calculated and measured harmonic components of blade bending moments. These differences, moreover, were largely nullified when the harmonic components were combined to give a comparison of the calculated and measured blade total- moment time histories. The degree of agreement shown is therefore considered adequate to warrant the use of the theoretical method in establishing and applying methods of prediction of rotor-blade fatigue loads. At the same time, the validity of the experimental methods of obtaining both airload and blade stress measurement is also indicated to be adequate for use in establishing improved methods for prediction of rotor-blade fatigue loads during the design stage. The blade stiffnesses and natural frequencies were measured and found to be in close agreement with calculated values; however, for a condition of blade resonance the use of the experimental stiffness values resulted in better agreement between calculated and measured blade stresses.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-2-28-59L , L-140
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  • 49
    Publication Date: 2019-08-15
    Description: As a continuation of an investigation of the release characteristics of an MB-1 rocket carried internally by the Convair F-106A airplane, six missile-bay baffle configurations and a rocket end plate have been investigated in the 27- by 27-inch preflight jet of the NASA Wallops Station. The MB-1 rocket used had retractable fins and was ejected from a missile bay modified by the addition of six different baffle configurations. For some tests a rocket end plate was added to the model. Dynamically scaled models (0.04956 scale) were tested at a simulated altitude of 22,450 feet and Mach numbers of 0.86, 1.59, and 1.98, and at a simulated altitude of 29,450 feet and a Mach number of 1.98. The results of this investigation indicate that the missile-bay baffle configurations and the rocket end plate may be used to reduce the positive pitch amplitude of the MB-1 rocket after release. The initial negative pitching velocity applied to the MB-1 rocket might then be reduced in order to maintain a near-level-flight attitude after release. As the fuselage angle of attack is increased, the negative pitch amplitude of the rocket is decreased.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-4-29-59L , AF-AM-57 , L-361
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  • 50
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    In:  CASI
    Publication Date: 2019-08-14
    Description: No abstract available
    Keywords: AERODYNAMICS
    Type: MSF-TN-J-13-59 , BAC-7021-3252-002
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  • 51
    Publication Date: 2019-08-15
    Description: A series of landings was performed with a straight-wing airplane to evaluate the effect of low lift-drag ratios on approach and landing characteristics. Landings with a peak lift-drag ratio as low as 3 were performed by altering the airplane configuration (extending speed brakes, flaps, and gear and reducing throttle setting). As lift-drag ratio was reduced, it was necessary either to make the landing pattern tighter or to increase initial altitude, or both. At the lowest lift-drag ratio the pilots believed a 270 deg overhead pattern was advisable because of the greater ease afforded in visually positioning the airplane. The values of the pertinent flare parameters increased with the reduction of lift-drag ratio. These parameters included time required for final flare; speed change during final flare; and altitude, glide slope, indicated airspeed, and vertical velocity at initiation of final flare. The pilots believed that the tolerable limit was reached with this airplane in the present configuration, and that if, because of a further reduction in lift-drag ratio, more severe approaches than those experienced in this program were attempted, additional aids would be required to determine the flare-initiation point.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-X-31
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  • 52
    Publication Date: 2019-08-15
    Description: Values of the normal component of induced velocity throughout the entire field of a uniformly loaded r(rotor at high high speed are presented in the form of charts and tables. Many points were found by an electromagnetic analog, details of which are given. Comparisons of computed and analog values for the induced velocity indicate that the latter are sufficiently accurate for engineering purposes.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TR-R-41
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  • 53
    Publication Date: 2019-08-15
    Description: This paper briefly summarizes available statistical data on airplane taxi operations, examines the profiles and power spectra of four selected runways and taxiways covering a wide range of surface roughness, considers (on the basis of theoretical and experimental results) the loads resulting from taxiing on such runways over a range of speeds and, by synthesis of the aforementioned results, proposes new criteria for runway and taxiway smoothness which are applicable to new construction and may also be used as a guide for determining when repairs are necessary.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-2-21-59L
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  • 54
    Publication Date: 2019-08-15
    Description: Flight tests have been conducted with a single-rotor helicopter, one blade of which was equipped at 14 percent and 40 percent of the blade radius with strain gages calibrated to measure moments rather than stresses, to determine the effects of transition, landing approaches, and partial-power vertical descents on the rotor-blade bending and torsional moments. In addition, ground tests were conducted to determine the effects of static droop-stop pounding on the rotor-blade moments. The results indicate that partial-power vertical descents and landing approaches produce rotor-blade moments that are higher than the moments encountered in any other flight condition investigated to date with this equipment. Decelerating through the transition region in level flight was found to result in higher vibratory moments than accelerating through this region. Deliberately induced static droop-stop pounding produced flapwise bending moments at the 14-percent-radius station which were as high as the moments experienced in landing approaches and partial-power vertical descents.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-5-7-59L
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  • 55
    Publication Date: 2019-08-15
    Description: Generalized influence coefficients are calculated by the method of NACA TN 3640 for a large-scale, built-up, 450 delta-wing specimen. These are used together with appropriate generalized masses to obtain the natural modes and frequencies in symmetric and antisymmetric free-free vibration. The resulting frequencies are compared with those obtained experimentally and are found to be consistently high. Possible sources of the disparities are discussed.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-2-1-59L
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  • 56
    Publication Date: 2019-08-15
    Description: Some blunt-body shapes considered suitable for entry into the earth's atmosphere were tested by both static and oscillatory methods in the Langley stability tunnel. In addition, free-fall tests of some similar models were made in the Langley 20-foot free-spinning tunnel. The results of the tests show that increasing the flare of the body shape increased the dynamic stability and that for flat-faced shapes increasing the corner radius increased the stability. The test data from the Langley stability tunnel were used to compute the damping factor for the models tested in the langley 20-foot free-spinning tunnel. For these cases in which the damping factor was low, -1/2 or less, the stability was critical and sensitive to disturbance. When the damping factor was about -2, damping was generally obtained.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-2-22-59L , L-157
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  • 57
    Publication Date: 2019-08-16
    Description: A preliminary investigation was conducted to determine whether a warhead stage of an antimissile missile could be placed within an arbitrary 2-nautical-mile-radius maneuver cylinder around an intercontinental-ballistic-missile (ICBM) flight path above an altitude of 140,000 feet, a horizontal range of 40 nautical miles, at a flight-path angle of approximately 20 deg, and within 50 seconds after take-off using only aerodynamic forces to turn the antimissile missile. The preliminary investigation indicated that an antimissile missile using aerodynamic forces for turning was capable of intercepting the ICBM for the stated conditions of this study although the turning must be completed below an altitude of approximately 70,000 feet to insure that the antimissile missile will be at the desired flight-path angle. Trim lift coefficients on the order of 2 to 3 and a maximum normal-acceleration force of from 25g to 35g were necessary to place the warhead stage in intercept position. The preliminary investigation indicated that for the two boosters investigated the booster having a burning time of 10 seconds gave greater range up the ICBM flight path than did the booster having a burning time of 15 seconds for the same trim lift coefficient and required the least trim lift coefficient for the same range.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-2-14-59L
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  • 58
    Publication Date: 2019-08-16
    Description: As a means of evaluating the roll utilization of a fighter airplane capable of supersonic speeds, an instrumented North American F-100A fighter airplane was flown by U.S. Air Force pilots at Nellis Air Force Base, NV, during 20 hours of service operational flying. Mach numbers up to 1.22 and altitudes up to 50,000 feet were realized in this investigation. Results of the study showed that except for high g barrel rolls performed as evasive maneuvers and rolls performed in acrobatic flying, rolling was utilized primarily as a means of changing heading. Acrobatic and air combat maneuvering produced the largest bank angles (1,200 deg), roll velocities (3.3 radians/sec), rolling accelerations (8 radians/sq sec) and sideslip angles (10.8 deg). Full aileron deflections were utilized on numerous occasions. Although high rolling velocities and accelerations also were experienced during several air-to-air gunnery missions, generally, air-to-air gunnery and air-to-ground gunnery and bombing required only two-thirds of maximum aileron deflection. The air-to-air gunnery and air combat maneuvers initiated from supersonic speeds utilized up to two-thirds aileron deflection and bank angles of less than 18 deg and resulted in rolling velocities and accelerations of 2 radians per second and 4.6 radians/sq sec, respectively. Rolling maneuvers were often initiated from high levels of normal acceleration, but from levels of negative normal acceleration only once.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-12-1-58H
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  • 59
    Publication Date: 2019-08-16
    Description: A flight investigation was undertaken to determine the effect of a fully controllable thrust reverser on the flight characteristics of a single-engine jet airplane. Tests were made using a cylindrical target-type reverser actuated by a hydraulic cylinder through a "beep-type" cockpit control mounted at the base of the throttle. The thrust reverser was evaluated as an in-flight decelerating device, as a flight path control and airspeed control in landing approach, and as a braking device during the ground roll. Full deflection of the reverser for one reverser configuration resulted in a reverse thrust ratio of as much as 85 percent, which at maximum engine power corresponded to a reversed thrust of 5100 pounds. Use of the reverser in landing approach made possible a wide selection of approach angles, a large reduction in approach speed at steep approach angles, improved control of flight path angle, and more accuracy in hitting a given touchdown point. The use of the reverser as a speed brake at lower airspeeds was compromised by a longitudinal trim change. At the lower airspeeds and higher engine powers there was insufficient elevator power to overcome the nose-down trim change at full reverser deflection.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-4-26-59A , A-135
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  • 60
    Publication Date: 2019-08-16
    Description: The first landing of the X-15 airplane was made at 8:43 a.m., June 8, 1959, on the hard surface of Rogers Dry Lake. One purpose of the first-glide flight was to evaluate the effectiveness of the landing-gear system. Some results are presented of the landing-approach characteristics, the impact period, and the runout phase of the landing maneuver. The results indicate that the touchdown was accomplished at a vertical velocity of 2.0 feet per second for the main gear and 13.5 feet per second for the nose gear. These vertical velocities were within the values of sinking speeds established by structural design limitations. However, permanent structural deformation occurred in the main-landing-gear system as a result of the landing, and a reevaluation of the gear is being made by the manufacturer. The landing occurred at a true ground speed of 158 knots for main-gear touchdown at an angle of attack of 8.50. The incremental acceleration at the main gear was 2.7g and 7.39 at the nose gear as a result of the landing. The incremental acceleration at the center of gravity of the airplane was 0.6g for the main-gear impact and 2.4g for the nose-gear impact. The incremental acceleration at the main gear as a result of the nose-gear impact was 4.8g. The extreme rearward location of the main-gear skids appears to offer satisfactory directional stability characteristics during the run- out phase of the landing. No evidence of nosewheel shimmy was indicated during the impact and runout phase of the landing despite the absence of a shimmy damper on the nose gear. The maximum amount of skid wear as a result of the landing was on the order of 0.005 inch. No appreciable amount of tire wear was indicated for the dual, corotating nosewheels.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-X-207
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  • 61
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 412-415 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959) 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 29-37 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 1-14 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Description / Table of Contents: Latest Developments in Antirust PaintingFor constructions made of steel a durable protection against rust can only be achieved if all factors conditioning the corrosive effects, especially the environmental influences like rain, dew, the dew point, temperature and agressiveness of the atmosphere, are considered. Their effects on the problem of priming and preliminary treatments of the surface (removal of scale and rust), on the efficiency of rust removers as well as on the protective value of wash primers are discussed. This is followed by information on the composition of protective paints, pigments and binders for priming and the composition of top coats; the specific aptitude of pigments, fillers and binders as well as on protective top paints.
    Notes: Ein dauerhafter Rostschutz von Stahlbauwerken setzt die Kenntnis aller sich auswirkenden Faktoren, insbesondere der Umwelteinflüsse wie Regeneinwirkung, Taubildung, Taupunkt, Temperatur und Aggressivität der Atmosphäre voraus. Ihre Auswirkung auf die Frage der Werksgrundierung, insbesondere der Untergrundvorbereitung (Entzunderung, Entrostung, Eignung) von Rostumwandlern und Schutzwert von Wash-Primern wird besprochen. Es folgen grundsätzliche Angaben über den Aufbau der Schutzanstrichmittel, Pigmente und Bindemittel für Grundierungen, über verschiedenartige Grundanstriche, über die Zusammensetzung der Deckanstriche, der spezifischen Eignung der Pigmente, Füllstoffe und Bindemittel, und über Rostschutz-Deckfarben.
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 38-40 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 26-29 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Description / Table of Contents: The Influence of Protective Colloids upon the Corrosion of BrassSome investigations showed that the corrosion of brass by acid plant substances is much lower than that caused by the corresponding vegetable acids of the same pH-value. The reason is obviously the presence of colloids in the plant matter. The article presents the results of investigations on the effects of protective colloids like pulvis acacia, e.g. albumin, agar, dextrine and potato starch upon the corrosion of brass in citric acid, hydrochloric acid and sulfuric acid. The data are represented in chart form. The protective effects of the various colloids differ very much according to the combination of colloid and acid. While an essential decrease of corrosion took place in citric acid solutions which is explained by an adsorption of colloid on the metal surface and the formation of a protective cover, the rate of corrosion was increased if hydrochloric acid was used even at constant concentration of colloids. Here dezincification took place which means that the more basic metal suffered a more intensive corrosive attack. The authors believe that protection in hydrochloric solutions could be achieved if a higher concentration of the colloid were used.
    Notes: Bei Forschungsarbeiten war gefunden worden, daß die Korrosion von Messing durch säuernde pflanzliche Substanzen geringer war als die durch die entsprechenden Fruchtsäuren mit gleichem pH verursachte Korrosion. Der Grund der Herabsetzung war offenbar der Kolloidgehalt der Pflanzen und in der vorliegenden Arbeit werden die Resultate von Untersuchungen über die Einwirkung derartiger Schutzkolloide wie Pulvis Acacia, Ei-Albumin, Agar, Dextrin und Kartoffelstärke auf die Korrosion von Messing in Zitronensäure, Salzsäure und Schwefelsäure vorgelegt. Das Material wurde in Tabellen zusammengestellt. Es zeigte sich, daß die Schutzwirkung der verschiedenen Kolloide sehr unterschiedlich war, sowohl in Bezug auf die Kolloide selbst als auch auf die angewandten Säuren. Während sich bei Zitronensäure deutliche Schutzwirkung durch Herabsetzung der Korrosion einstellte, die durch Adsorption des Kolloids an das Metall und Bildung eines Schutzfilms erklärt wird, wurde bei Salzsäure die Korrosion erhöht, wenn die gleichen Kolloidkonzentrationen angewendet wurden und es trat “Entzinkung” ein, d. h., das basische Metal wurde stärker angegriffen. Die Verfasser sind der Meinung, daß bei Verwendung höherer Kolloidkonzentrationen auch bei Salzsäure Schutzwirkung eintreten würde.
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  • 67
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Description / Table of Contents: On the Electro-Deposition of Titanium from Aqueous Solutions of Potassium-Titanium-FluorideAs discerned from current density-voltage curves titanium can be deposited from aqueous solutions of potassium titanium fluoride. The deposition of the metal takes place by the formation of TiO++ ions and their reduction by nascent hydrogen. The cathode must consist of metals with high overvoltage. On aluminium cathodes deposition of titanium and passivation by aluminium and titanium hydroxides take place simultaneously.The effects are in agreement with the law of the formation of surface covers by Müller Machu. The current yields are very low. Though they would not exceed 30 pct. the current yields of this method are higher than ever before when other titaniums salts are used.On zinc cathodes there is no passivation. So the percentage of the metallic titanium in the deposition is higher than on aluminum cathodes. Micro-photographs demonstrate the influences of additives like gelatin, thiourea etc. which suppress the formation of hydroxides and oxides in the deposition. The formation thick deposits of titanium which are free from oxides is still meeting difficulties.
    Notes: Titan läßt sich, wie anhand von Strom-Spannungskurven gezeigt wird, aus dem Kaliumtitanfluorid in wäßriger Lösung abscheiden. Dabei erfolgt die Metallabscheidung auf dem Umweg über die Bildung von Ti2+-Ionen und durch Reduktion durch naszierenden Wasserstoff. Als Kathodenmaterial sind nur Metalle mit hoher Überspannung geeignet. An Aluminiumkathoden erfolgt während der Titanabscheidung auch eine Passivierung durch Aluminium- und Titanhydroxyd, wobei das Flächenbedeckungsgesetz von Müller-Machu erfüllt ist. Die Stromausbeuten sind nur gering, sie übersteigen 30% nicht, sind aber weit größer als dies mit anderen Titansalzlösungen bisher möglich war.An Zinkkathoden fehlt die Passivierung, daher ist der Anteil an metallischem Titan im Niederschlag größer als an Aluminium. Anhand von Mikrophotos wird der Einfluß von Zusätzen wie Gelatine, Thiobarnstoff u. dergl. aufgezeigt, welche die Bildung von Hydroxyd und Oxyd im Niederschlag unterdrücken. Die Herstellung dickerer Titanniederschläge, frei von Oxyden, bereitet noch Schwierigkeiten.
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 41-42 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 43-48 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 49-56 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 57-57 
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    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 57-57 
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    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 57-59 
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    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 60-62 
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    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 62-64 
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    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 64-64 
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    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 64-64 
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    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. I 
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    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 65-65 
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    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 70-73 
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    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Description / Table of Contents: Contribution to the Development of Neoprenes for the Protection or Chemical InstrumentsThe process of coating equipment with prevulcanised Neoprene plates as ex- plained in its various stages. In addition, seven cases are described in which such coatings have been found satisfactory in practice.
    Notes: Das Verfahren der Auskleidung von Apparaten mit vorvulkanisierten Neoprene-Platten wird in seinen einzelnen Stufen erläutert. Anschließend werden 7 Fälle beschrieben, in denen sich diese Auskleidungen bewährt haben.
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 66-70 
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    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Description / Table of Contents: Practical Experiences in the Corrosion Behavior of Zinc PaintsGeneral survey of zinc paints.Conditions of technical application.Preliminary treatment of iron surfaces.Comparison of the test results of various dust paints by different testing methods.Report on experiences with zinc dust paints in steel construction building, open air constructions and in steel sheet working industries.
    Notes: Allgemeines über Zinkanstrichmittel; Verarbeitungstechnische Erfordernisse; Vorbehandlung der Eisenoberfläche.Vergleichende Gegenüberstellung von Testergebnissen mit unterschiedlichen Zinkstaubfarben nach verschiedenen Testverfahren.Praktische Erfahrungen mit Zinkstaubfarben im allgemeinen Stahlhochbau, bei Freiluftkonstruktionen und in der Stahlblech-verarbeitenden Industrie.
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 74-77 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Description / Table of Contents: High Temperature Corrosion in Petrol Refining by Sulfur CompoundsAt temperatures above 260°C only stainless, highly alloyed steels resist the attack of the most corrosive agent in petrol refining which is hydrogen sulfide. For high temperature corrosion by hydrogen sulfide, the influences of the duration of wear, the concentration of the hydrogen sulfide, the pressure, the properties of the refined petrol and the quality of the steel are of essential importance besides of the effects of temperature. The author reports on last years investigations in BP-research station on the corrosion of stainless steels by hydrogen sulfide at high temperatures. The corrosion of the surface, the inter-crystalline corrosion and the stress corrosion of steels are discussed in detail.
    Notes: Dem Angriff des wesentlichsten korrosiven Agens in Erdölraffinerien, dem Schwefelwasserstoff, bei hohen Temperaturen (über 260°C) widerstehen praktisch ausschließlich rostfreie, hochlegierte Stähle. Bei der Hochtemperatur-Korrosion durch Schwefelwasserstoff sind neben der Temperatur auch Beanspruchungsdauer, Schwefelwasserstoff konzentration, Druck, Beschaffenheit des zu raffinierenden Öles und die Stahlqualität von Einfluß. Verfasser berichtet über die in den letzten Jahren in der BP-Research Station durchgeführten Untersuchungen über die Korrosion von rostfreien Stählen durch Schwefelwasserstoff bei hohen Temperaturen, wobei allgemeine Oberflächen-korrosion, interkristalline Korrosion und Spannungskorrosion der Stähle eingebend behandelt werden.
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  • 83
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Description / Table of Contents: New Investigations into Hydrogen Adsorption and Dissolved IronThe solution processes of iron in n HCl were investigated and a correlation was found between the quantity of hydrogen absorbed in the iron and the rate at which the metal dissolved. A dynamical saturation equilibrium was established in the interior of the metal. From this the significance of partial reactions can be derived and the action of inhibitors explained.
    Notes: Es wurden die Auflösungsvorgänge von Eisen in In-HCL untersucht und ein Zusammenhang zwischen der Menge des vom Eisen aufgenommenen Wasserstoffs und der Auflösungsgeschwindigkeit des Metalls gefunden. Es stellt sich dabei ein dynamisches Sättigungsgleichgewicht im Innern des Metalls ein. Daraus läßt sich die Bedeutung der Teil-Reaktionen ableiten und das Eingreifen von Inhibitoren erklären.
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  • 84
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Description / Table of Contents: Investigations of Pitting on Highly Alloyed Austenitic Chrome Nickel Steels and Ferritic Chrome Steels in Aqueous Solutions Containing HalidesTbe application of stainless steels in aqueous solutions containing halides is limited.The authors show that it is not the corrosion potential, determined by means of the generally applied test in a 10 pct. FeCl3-solution, but the slope of the potential vs. current density as a electrochemical data which indicates the sensitivity to pitting.The K3[Fe(CN)6]-test has proved to be a good quick method. By means of this method pitting is indicated as a active passive reaction.Pitting occurs only at potentials within a certain range which can be determined from a current density-voltage curve.In a 5 pct. sulfuric acid containing air, at room temperature the uniform transpassive dissolution of steel takes place only. In sulfuric acid solutions containing chlorides steel is corroded uniformly in its active state or by pitting but not transpassively. An addition of nitrate to such a solution inhibits pitting but increases the transpassive corrosion.
    Notes: Die Einsatzmöglichkeit der chemisch beständigen Stähle in halogenidhaltigen, wäßrigen Medien wird durch die Erscheinung der Lochfraßkorrosion eingeschränkt.Es wird gezeigt, daß bei der allgemein üblichen Prüfung in einer 10%igen FeCl3-Lösung für die Lochfraßanfälligkeit nicht das Korrosionspotential, sondern der Polarisationswiderstand als elektrochemische Meßgröße kennzeichnend ist.Als praktisches Schnellprüfverfahren hat sich der K3[Fe(CN)6]-Test bewährt. Mit Hilfe dieser chemischen Indikation wird der Lochfraß-Mechanismus als Aktiv-Passiv-Reaktion bewiesen. Das Auftreten der Lochfraßkorrosion ist an einen gewissen Potentialbereich gebunden, der durch Messung der Stromdichte-Potential-Kurve bestimmt werden kann.In reiner lufthaltiger 5%iger Schwefelsäure ist bei Raumtemperatur nur die gleichmäßig transpassive Stahlauflösung möglich. In chloridhaltiger Schwefelsäure kann der Stahl gleichmäßig aktiv oder durch Lochfraß, dagegen nicht transpassive korrodieren. Durch einen Nitratzusatz zur chloridhaltigen Schwefelsäure wird die Lochfraßkorrosion zugunsten der transpassiven Korrosion inhibitiert.
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  • 85
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 106-110 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 86-91 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Description / Table of Contents: On the Photo-Chemistry of Metallic Copper and its Influence on the Velocity of the Dissolution of Copper as ElectrodeBy etching copper with a mixture of nitric and hydrochloric acid, a sensitive layer is formed which is blackened according to the duration of the exposion to light. An exposion by means of a 6,7 V-incandescent lamp at a distance of 10 cm from the copper surface generates a spot of 1,75 cm2 surface. Three discontinuities occur in certain intervals. The intensity of the reflexion was measured by means of a photoelectric cell and a mirror-galvanometer. Increase of temperature causes a decrease of the velocity of blackening the sensitive layer. Observing the influence of light upon the velocity of the dissolution of copper we obtained a typical dependance of the velocity of corrosion on the photochemical reaction on the copper surface.
    Notes: Durch Ätzung von Kupfer mit einem HNO3-HCl-Gemisch entsteht eine photoaktive Kupferschicht, die nach Belichtung eine zeitlich abhängige Schwärzung aufweist. Bei der Belichtung mit einer 6,7 V-Glühlampe in einem Abstand von 10 cm wird auf der Kupferoberfläche ein Lichtfleck von etwa 1,75 cm2 gebildet. In bestimmten Zeitintervallen treten sodann drei Diskontinuitäten auf. Die Intensität der Reflexion wurde mit Photozelle und Spiegelgalvanometer registriert. Die Erhöhung der Temperatur führt zur Verminderung der Schwärzungsgeschwindigkeit der photoaktiven Schicht.Die Beobachtungen über den Einfluß des Lichtes auf die Auflösungsgeschwindigkeit des Kupfers in Elektrolyten ergaben eine typische Abhängigkeit der Korrosionsgeschwindigkeit von der an der Kupfer-Oberfläche stattgefundenen Reaktion.
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 111-115 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 116-121 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 122-122 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
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  • 90
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 121-122 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
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  • 91
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Description / Table of Contents: Investigations on the Corrosion Behavior of Aluminum and Aluminum Alloys upon Organic and Inorganic BasesThe article presents a comparison of the corrosive effects of organic and inorganic bases upon aluminium materials by means corrosion tests carried out at a temperature of 20°C for 73hrs. The aggressivity of the bases investigated decreases in the order of sodium hydroxide, methylamine, ethylamine, n-butylamine, ammonia, triethanolamine, sodium carbonate, calcium hydroxide, hydrazine. The sensitivity to corrosion of the materials decrease in the order of pure aluminium A1 99,3, purest aluminium Raffinal raf W(more than 99,99% Al) anticorodal Ac B, Avional Av-23 V, Perunal Pu V and Peraluman Pe-30 W. For every mixture of a base and water, there is a critical concentration at which the intensity of the attack reacher its maximum. High concentrated bases cause but low corrosion and anhydrous bases are fairly inactive. There is no destinct relationship between the corrosion behavior of the bases and their pH-values resp. their electric conductivity.
    Notes: In der vorliegenden Abhandlung wird auf Grund von bei 20°C durchgeführten 73stündigen Korrosionsversuchen mit verschiedenen Aluminiumwerkstoffen die aluminiumangreifende Wirkung organischer Basen mit der anorganischer verglichen. Die Aggressivität der untersuchten Basen nimmt in der anorganischer verglichen. Die Aggressivität der untersuchten Basen nimmt in der Reihenfolge Natriumhydroxyd, Methylamin, Aethylamin, n-Butylamin, Ammoniak, Triäthanolamin, Natriumcarbonat, Calciumhydroxyd, Hydrazin ab. Die Korrosionsfälligkeit einzelner Werkstoffe vermindert sich entsprechend der Reihe Reinaluminium Al 99,3, Reinstaluminium Raffinal Raf W (über 99,99% Al), Anticorodal Ac B, Avional Av-23 V, Perunal Pu V und Peraluman Pe-30 W. Bei jedem Gemisch Base/Wasser besteht eine kritische Konzentration, bei welcher die Intensität des Angriffs auf Aluminium ein Maximum erreicht. Sehr konzentrierte Basen wirken nur ganz schwach, wasserfreie Basen kaum aluminiumangreifend. Zwischen den Korrosionseigenschaften der einzelnen Basen und ihrem pH-Wert bzw. ihrer elektrischen Leitfähigkeit bestehen keine eindeutigen Zusammenhänge.
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 122-122 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 123-127 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 127-137 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
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    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 138-138 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 139-139 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
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    Keywords: Chemistry ; Polymer and Materials Science
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 139-141 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
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    Materials and Corrosion/Werkstoffe und Korrosion 10 (1959), S. 141-144 
    ISSN: 0947-5117
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Additional Material: 18 Ill.
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