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  • Industrial Chemistry  (514)
  • Life and Medical Sciences  (261)
  • Aircraft Design, Testing and Performance  (38)
  • Aircraft Stability and Control  (18)
  • Aircraft Propulsion and Power  (17)
  • Pflanzenschädling  (12)
  • 1950-1954  (387)
  • 1945-1949  (473)
  • 1930-1934
  • 1910-1914
  • 1952  (387)
  • 1949  (473)
Collection
Keywords
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  • 1950-1954  (387)
  • 1945-1949  (473)
  • 1930-1934
  • 1910-1914
Year
  • 1
    Publication Date: 1952
    Description: Vergleich des täglichen Flugverhaltens der Aphiden Doralis fabae und Myzodes persicae (Zweigipfelige Kurve) mit der Psyllide Trioza nigricornis (Eingipfelige Kurve). Die Prozentuale Verteilung der Blattläuse auf verschiedene Flughöhen wird analysiert. Die Abhängigkeit des Flugverhaltens der Blattläuse von den Faktoren Licht, Wind,Temperatur, relative Luftfeuchte wird untersucht. Zudem wird deren kombinierte Wirkung auf den Flug der Homopteren untersucht und im Zuge dessen die drei Homopteren in drei verschiedene Reaktionstypen eingeordnet. KATASTER-BESCHREIBUNG: Grenzwert der Windgeschwindigkeit für den aktiven Abflug von Aphidae und Psyllidae. Regressionsgleichungen für den Zusammenhang zwischen Temperatur und Flugtätigkeit der beiden Aphidae (T(200)=Temperatur in 2m Höhe; T(10)=Temperatur in 10 cm Höhe); Multipler Korrel.koeff. zwischen Temp., modif. rel. Luftf. und dem aktiven Anflug von Trioza nigricornis R=0,742; Zusammenhang der Flugtätigkeit von T. nigricornis und Temp, ist linear -〉 siehe Korrelationstabelle KATASTER-DETAIL: Wind 〉3km/h dann aktiver Abflug Aphiden = 0; Delta T (2m;〈18,46°C) + oder Delta T (2m;〉18,46°C) - oder Delta T (10cm;〈17,18°C) + oder Delta T (10cm;〉17,18°C) - dann Flugtätigkeit M.persicae + ;Delta T (2m;〈19,32°C) + oder Delta T (2m;〉19,32°C) - oder Delta T (10cm;〈19,5°C) + oder Delta T (10cm;〉19,5°C) - dann Flugtätigkeit D.fabae + ;Delta T + und Delta relf (bis 60-70%) - dann Anflug T.nigricornis + Regressionsgleichungen für Myzodes persicae: Flugtätigkeit(FT)=-136,19 + 16,61*T(200) - 0,45*T(200)²; FT=-95,62 + 13,74*T(10) - 0,40*T(10)²; Regressionsgleichungen für Doralis fabae: FT=-62,56 + 8,075*T(200) - 0,209*T(200)²; FT=-93,29 + 11,193*T(10) - 0,287*T(10)²;
    Keywords: Quedlinburg, Thüringen ; 1951 ; Tabak ; Getreide ; Pflanzenschädling ; Hackfrüchte ; Obst ; Zierpflanzen ; Gemüse
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  • 2
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    In:  Mitteilungen aus der Biologischen Zentralanstalt für Land- und Forstwirtschaft Berlin-Dahlem, Heft 73
    Publication Date: 1952
    Description: 4-jährige Feldexperimente und -beobachtungen zum winterlichen Massenwechsel der grünen Pfirsichblattlaus KATASTER-BESCHREIBUNG: Entscheidende Faktoren für Vorkommen und Ausmaß der anholozyklischen Überwinterung KATASTER-DETAIL: Delta T-: T(Bodennähe)〈= -5°C, dann Myzodes persicae -; Winterfröste: Dauer + , zeitiger, Minimum -, dann Myzodes persicae -; Nachwinter: Delta T + und Delta Nied -, dann Myzodes persicae +
    Keywords: Kölner Bucht ; 1948 - 1951 ; Pflanzenschädling ; Temperatur
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  • 3
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    Unknown
    In:  Gesunde Pflanzen 4, Heft 10; p.274-277
    Publication Date: 1952
    Description: Eine kurze Zusammenfassung der Einsparungen durch nicht benötigte Traubenwickler- und Peronosporabekämpfungen in der Pfalz im Jahre 1952 wird gegeben. Hierfür werden große Hitze und Trockenheit im Jahre 1952 im Vergleich zum Vorjahr und zum 31-jährigen Mittel als Ursache genannt. Die Prognose wurde durch Beobachtungen erstellt. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Pfalz ; 1951-1952 ; Pflanzenkrankheit ; Pflanzenschädling ; Wein
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  • 4
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    Unknown
    In:  Beiträge zur Entomologie, Band 2, Nr. 2/3, p. 256-315
    Publication Date: 1952
    Description: Beobachtungen und Untersuchungen zur Biologie, Epidemiologie und Bekämpfung des Rübenderbrüßlers KATASTER-BESCHREIBUNG: Einflüsse der Witterung auf die Entwicklung und das Massenauftreten des Käfers KATASTER-DETAIL: Delta T und Delta Nied und Delta Sonn: T(Boden)〉8°C und Delta Nied -, Delta T (Luft) + und Delta Sonn +, dann Verlassen des Bodens; Delta T -, dann Unterbrechungen der Abwanderung +; Delta T und Delta Sonn: T〉=22°C und Sonnenschein, dann Flug; Delta T: T〉= 15-17°C, dann Reifung; T=26,2°C und Relf=30-37%, dann maximale Eizahl; T〈2°C, dann Erstarrungszustand; Delta Nied (Mai, Juni) -, dann Massenauftreten +; Delta T +, dann Eizahl +;
    Keywords: Sachsen-Anhalt ; 1950 ; Zuckerrüben ; Boden ; Niederschlag ; Pflanzenschädling ; Temperatur ; Witterung ; Sonnenscheindauer
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  • 5
    Publication Date: 2019-06-28
    Description: A cascade of 65-(12)10 compressor blades was tested at one geometric setting over a range of inlet Mach number from 0.12 to 0.89. Two groups of data are presented and compared: the first from the cascade operating conventionally with no boundary-layer control, and the second with the boundary layer controlled by a combination of upstream slot suction and porous-wall suction at the blade tips. A criterion for two-dimensionality was used to specify the degree of boundary-layer control by suction to be applied. The data are presented and an analysis is made to show the effect of Mach number on turning angle, blade wake, pressure distribution about the blade profile and static-pressure rise. The influence of boundary-layer control on these parameters as well as on the secondary losses is illustrated. A system of correlating the measured static-pressure rise through the cascade with the theoretical isentropic values is presented which gives good agreement with the data. The pressure distribution about the blade profile for an inlet Mach number of 0.21 is corrected with the Prandtl-Glauert, Karman-Tsien, and vector-mean velocity - contraction coefficient compressibility correction factors to inlet Mach numbers of 0.6 and 0.7. The resulting curves are compared with the experimental pressure distributions for inlet Mach numbers of 0.6 and 0.7 so that the validity of applying the three corrections can be evaluated.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-2649
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  • 6
    Publication Date: 2019-07-11
    Description: The static longitudinal stability characteristics of a 0.15-scale model of the Hermes A-lE2 missile have been determined in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.50 to 0.98, corresponding to Reynolds numbers, based on body length, of 12.3 x 10(exp 6) to 17.1 x 10(exp 6). This paper presents results obtained with body alone and body-fins combinations at 0 degrees (one set of fins vertical and the other set horizontal) and 45 degree angle of roll. The results indicate that the addition of the fins to the body insures static longitudinal stability and provides essentially linear variations of the lift and pitching moment at small angles of attack throughout the Mach number range. The slopes of the lift and pitching-moment curves vary slightly with Mach number and show only small effects due to the angle of roll.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL52I10
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  • 7
    Publication Date: 2019-07-11
    Description: At the request of the Bureau of Aeronautics, Department of the Navy, an investigation at transonic and low supersonic speeds of the drag and longitudinal trim characteristics of the Douglas XF4D-1 airplane is being conducted by the Langley Pilotless Aircraft Research Division. The Douglas XF4D-1 is a jet-propelled, low-aspect-ratio, swept-wing, tailless, interceptor-type airplane designed to fly at low supersonic speeds. As a part of this investigation, flight tests were made using rocket- propelled 1/10- scale models to determine the effect of the addition of 10 external stores and rocket packets on the drag at low lift coefficients. In addition to these data, some qualitative values of the directional stability parameter C(sub n beta) and duct total-pressure recovery are also presented.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL52G11
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  • 8
    Publication Date: 2019-07-11
    Description: An investigation of a vortex-generator configuration on the wings of a l/4-scale model of the X-1 airplane having a 10-percent-thick wing was conducted in the Langley 16-foot transonic tunnel. The effect of the vortex generators was determined by comparing the model aerodynamic characteristics, wing-pressure distributions, and wing-wake patterns for model configurations with and without vortex generators on the wings. Results are presented from tests at 0.1 increments in Mach number from about 0.69 to 0.99, at Reynolds numbers of about 4.1 x 10(exp 6) to 4.7 x 10(exp 6), and through an angle-of-attack range up to 1.5 deg at lower speeds and up to 5 deg at the highest speed. In general, little difference in the aerodynamic characteristics was observed, except at a Mach number of 0.90 where a rearward movement of the shock on the upper surface of the wing with the vortex generators installed resulted in less separation.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-L52L26
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  • 9
    Publication Date: 2019-07-12
    Description: An investigation to increase the compressor surge-limit pressure ratio of the XJ40-WE-6 turbojet engine at high equivalent speeds was conducted at the NACA Lewis altitude wind tunnel. This report evaluates the compressor modifications which were restricted to (1) twisting rotor blades (in place) to change blade section angles and (2) inserting new stator diaphragms with different blade angles. Such configuration changes could be incorporated quickly and easily in existing engines at overhaul depots. It was found that slight improvements in the compressor surge limit were possible by compressor blade adjustment. However, some of the modifications also reduced the engine air flow and hence penalized the thrust. The use of a mixer assembly at the compressor outlet improved the surge limit with no appreciable thrust penalty.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE52G03
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  • 10
    Publication Date: 2019-07-12
    Description: The stator-blade angles in the twelfth through fifteenth stages of a 16-stage axial-flow compressor were increased 3O. The over-all performance of this modified compressor is compared to the performance of the compressor with original blade angles. The matching characteristics of the modified compressor and a two-stage turbine were obtained and compared to those of the compressor with original blade angles and the same turbine.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E52A10
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  • 11
    Publication Date: 2019-08-14
    Description: An impulse-momentum method for determining impact conditions for landing gears in eccentric landings is presented. The analysis is primarily concerned with the determination of contact velocities for impacts subsequent to initial touchdown in eccentric landings and with the determination of the effective mass acting on each landing gear. These parameters determine the energy-absorption requirements for the landing gear and, in conjunction with the particular characteristics of the landing gear, govern the magnitude of the ground loads. Changes in airplane angular and linear velocities and the magnitude of landing-gear vertical, drag, and side impulses resulting from a landing impact are determined by means of impulse-momentum relationships without the necessity for considering detailed force-time variations. The effective mass acting on each gear is also determined from the calculated landing-gear impulses. General equations applicable to any type of eccentric landing are written and solutions are obtained for the particular cases of an impact on one gear, a simultaneous impact on any two gears, and a symmetrical impact. In addition a solution is presented for a simplified two-degree-of-freedom system which allows rapid qualitative evaluation of the effects of certain principal parameters. The general analysis permits evaluation of the importance of such initial conditions at ground contact as vertical, horizontal, and side drift velocities, wing lift, roll and pitch angles, and rolling and pitching velocities, as well as the effects of such factors as landing gear location, airplane inertia, landing-gear length, energy-absorption efficiency, and wheel angular inertia on the severity of landing impacts. -A brief supplementary study which permits a limited evaluation of variable aerodynamic effects neglected in the analysis is presented in the appendix. Application of the analysis indicates that landing-gear impacts in eccentric landings can be appreciably more severe than impacts in symmetrical landings with the same sinking speed. The results also indicate the effects of landing-gear location, airplane inertia, initial wing lift, side drift velocity, attitude, and initial rolling velocity on the severity of both initial and subsequent landing-gear impacts. A comparison of the severity of impacts on auxiliary gears for tricycle and quadricycle configurations is also presented.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-2596
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  • 12
    Publication Date: 2019-07-11
    Description: An investigation was conducted at simulated high-altitude flight conditions to evaluate the use of compressor evaporative cooling as a means of turbojet-engine thrust augmentation. Comparison of the performance of the engine with water-alcohol injection at the compressor inlet, at the sixth stage of the compressor, and at the sixth and ninth stages was made. From consideration of the thrust increases achieved, the interstage injection of the coolant was considered more desirable preferred over the combined sixth- and ninth-stage injection because of its relative simplicity. A maximum augmented net-thrust ratio of 1.106 and a maximum augmented jet-thrust ratio of 1.062 were obtained at an augmented liquid ratio of 2.98 and an engine-inlet temperature of 80 F. At lower inlet temperatures (-40 to 40 F), the maximum augmented net-thrust ratios ranged from 1.040 to 1.076 and the maximum augmented jet-thrust ratios ranged from 1.027 to 1.048, depending upon the inlet temperature. The relatively small increase in performance at the lower inlet-air temperatures can be partially attributed to the inadequate evaporation of the water-alcohol mixture, but the more significant limitation was believed to be caused by the negative influence of the liquid coolant on engine- component performance. In general, it is concluded that the effectiveness of the injection of a coolant into the compressor as a means of thrust augmentation is considerably influenced by the design characteristics of the components of the engine being used.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E52F20
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  • 13
    Publication Date: 2019-07-11
    Description: An elementary type of analysis has been used to determine the amount of wing tip that must be severed to produce irrevocable loss of control of a B-29 airplane. The remaining inboard structure of the Boeing B-29 wing has then been analyzed and curves are presented for the estimated reduction in structural strength due to four general types of damage produced by rod-type warhead fragments. The curves indicate the extent of structural damage required to produce a kill of the aircraft within 10 seconds.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L52H01A
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  • 14
    Publication Date: 2019-07-10
    Description: An investigation was made of the performance of nine conical cooling-air ejectors at primary jet pressure ratios from 1 to 10, secondary pressure ratios to 4.0, and a temperature ratio of unity. This phase of the investigation was limited to conical ejectors having shroud exit to primary nozzle exit diameter ratios of 1.06 and 1.40, with several spacing ratios for each. The experimental results indicated that the pumping range and amount of cooling-air flow obtained with a 1.06 diameter ratio ejector were relatively small for cooling purposes but that the maximum possible thrust loss, which occurred with no secondary flow, was only 7 percent of convergent nozzle thrust. The 1.40 diameter ratio ejector produced a large cooling air flow and showed a possible thrust loss of 29.5 percent with no cooling air flow. Thrust gains were attained with ejectors of both diameter ratios at secondary pressure ratios greater than 1.0. The limiting primary pressure ratio below which an ejector can operate at a specific secondary pressure ratio (cut-off point) may be estimated for various flight conditions from data contained herein.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E52F26
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  • 15
    Publication Date: 2019-07-11
    Description: As part of a program to determine the feasibility of using a fighter airplane as a parasite in combination with a Consolidated Vultee RB-36 for long-range reconnaissance missions (project FICON), an experimental investigation has been made in the Langley free-flight tunnel to determine the dynamic stability and control characteristics of a 1/17.5-scale model of a Chance Vought F7U-3 airplane in several tow configurations. The investigation consisted of flight tests in which the model was towed from a strut in the tunnel by a towline and by a direct coupling which provided complete angular freedom. The tests with the direct coupling also included a study of the effect of spring restraint in roll in order to simulate approximately the proposed full-scale arrangement in which the only freedom is that permitted by the flexibility of the launching and retrieving trapeze carried by the-bomber. For the tow configurations in which a towline was used (15 and 38 feet full scale), the model had a very unstable lateral oscillation which could not be controlled. The stability was also unsatisfactory for the tow configuration in Which the model was coupled directly to the strut with complete angular freedom. When spring restraint in roll was added, however, the stability was satisfactory. The use of the yaw damper which increased the damping in yaw to about six times the normal value of the model appeared to have no appreciable effect on the lateral oscillations in the towline configurations, but produced a slight improvement in the case of the direct coupling configurations. The longitudinal stability was satisfactory for those cases in which the lateral stability was good enough to permit study of longitudinal motions.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL53D07
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  • 16
    Publication Date: 2019-07-11
    Description: An investigation of a 1/24-scale model of the Grumman F9F-6 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The erect and inverted spin and recovery characteristics of the model were determined for the normal flight loading with the model in the clean condition. The effect of loading variations was investigated briefly. Spin-recovery parachute tests were also performed. The results indicate that erect spins obtained on the airplane in the clean condition will be satisfactorily terminated for all loading conditions provided full rudder reversal is accompanied by moving the ailerons and flaperons (lateral controls) to full with the spin (stick right in a right spin). Inverted spins should be satisfactorily terminated by full reversal of the rudder alone. The model tests indicate that an 11.4-foot (laid-out-flat diameter) tail parachute (drag coefficient approximately 0.73) should be effective as an emergency spin-recovery device during demonstration spins of the airplane provided the towline is attached above the horizontal stabilizer.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL52G03A
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  • 17
    Publication Date: 2019-07-11
    Description: An investigation has been conducted in the Langley 20-foot free-spinning tunnel on a l/20-scale model of the Consolidated Vultee XFY-1 airplane with a windmilling propeller simulated to determine the effects of control setting and movements upon the erect spin and recovery characteristics for a range of airplane-loading conditions. The effects on the model's spin-recovery characteristics of removing the lower vertical tail, removing the gun pods, and fixing the rudders at neutral were also investigated briefly. The investigation included determination of the size parachute required for emergency recovery from demonstration spins. The tumbling tendencies of the model were also investigated. Brief static force tests were made to determine the aerodynamic characteristics in pitch at high angles of attack. The investigation indicated that the spin and recovery characteristics of the airplane with propeller windmilling will be satisfactory for all loading conditions if recovery is attempted by full rudder reversal accompanied by simultaneous movement of the stick laterally to full with the spin (stick right in a right spin) and longitudinally to neutral. Inverted spins should be satisfactorily terminated by fully reversing the rudder followed immediately by moving the stick laterally towards the forward rudder pedal and longitudinally to neutral. Removal of the gun pods or fixing the rudders at neutral will not adversely affect the airplane's spin-recovery characteristics, but removal of the lower vertical tail will result in unsatisfactory spin-recovery characteristics. The model-test results showed that a 13.3-foot wing-tip conventional parachute (drag coefficient approximately 0.7) should be effective as an emergency spin-recovery device during demonstration spins of the airplane. It was indicated that the airplane should not tumble and that no unusual longitudinal-trim characteristics should be obtained for the center-of-gravity positions investigated.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL52L10
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  • 18
    Publication Date: 2019-07-11
    Description: Tests have been made at the Langley Aeronautical Laboratory on a 6000-horsepower propeller dynamometer installed at a ground test facility to determine the effect of a half-scale model of the Wright Aeronautical Development Center 30,000-horsepower whirl rig upon the aerodynamic characteristics of a three-blade NACA 10-(3)(062)-045 propeller. The model of the whirl rig was mounted in front of the 6000-horsepower propeller dynamometer. Static propeller tests were made for 0deg, 5deg, 10deg, 15deg, and 20deg blade angles over a range of rotational speeds from 600 to 2200 rpm in 100-rpm increments. Measurements were made of propeller thrust and torque, stresses in the propeller blades, and static and total pressures over the surface of the model. Propeller thrust and torque were increased up to 33 percent by the presence of the model of the whirl rig, but the average increase was from 5 to 10 percent. Blade vibratory stresses were small.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL52F20
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  • 19
    Publication Date: 2019-07-11
    Description: The aerodynamic characteristics in pitch of the Army Ordnance Corps T205 3.5-inch HEAT rocket with various head designs and one fin modification have been determined at velocities of 500, 700 and 900 feet per second in the Langley high-speed 7- by 10-foot tunnel. The results presented are those of the full-scale model. Comparison of results obtained at 500 feet per second shows, in general, that for changes on the forward portion of the head the missile configurations having the greatest stability - most rearward center-of-loads location - were those having the highest drag. However, very limited comparisons indicate that the shape of the rear position of the head may be an important factor in reducing the drag and increasing the restoring moments. Generally, large increases in drag were noted for the various head designs with an increase in Mach number from 0.62 to 0.82. Pitching-moment-curve slopes increased with Mach number on all models except those having reasonably well-faired forward sections. These models showed a decrease in stability with increases in Mach number.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL52G15
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  • 20
    Publication Date: 2019-07-11
    Description: Preliminary results of one phase of a control-motion study program are presented in the form of plots of load factor.and angular acceleration against indicated airspeed and of time histories of several measured quantities. The results were obtained from 197 maneuvers performed by an F-86A jet-fighter airplane during normal squadron operational training. Most of the tactical maneuver8 of which the F-86A is capable were performed at pressure altitudes ranging from 0 to 32,000 feet and at indicated airspeeds ranging from 95 to 650 miles per hour.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L52C19
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  • 21
    Publication Date: 2019-07-12
    Description: Force characteristics determined from tank tests of a 1/5.78 scale model of a hydro-ski-wheel combination for the Grumman JRF-5 airplane are presented. The model was tested in both the submerged and planing conditions over a range of trim, speed, and load sufficiently large to represent the most probable full-size conditions.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SLS2B28
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  • 22
    Publication Date: 2019-07-12
    Description: The stator-blade angles in the twelfth to fifteenth stages of a 16-stage high-pressure-ratio axial-flow compressor were decreased 3 deg The over-all performance of this compressor is compared with the performance of the same compressor with standard blade angles. The matching characteristics of the modified compressor and a two-stage turbine were also obtained and compared with those of the compressor with the original blade angles and the same turbine.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E51L03
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  • 23
    Publication Date: 2019-07-12
    Description: A theoretical method for evaluating the stability characteristics and the amplitude and the frequency of pulsation of ram-jet engines without heat addition is presented herein. Experimental verification of the theoretical results are included where data were available. Theory and experiment show that the pulsation amplitude of a high mass-flow-ratio diffuser having no cone surface flow separation increases with decreasing mass flow. The theoretical trends for changes in amplitude, frequency, and mean-pressure recovery with changes in plenum-chamber volume were experimentally confirmed. For perforated convergent-divergent-type diffusers, a stability hysteresis loop was predicted on the pressure-recovery mass-flow-ratio curve. At a given mean mass-flow ratio, the higher.value of mean pressure recovery corresponded to oscillatory flow in the diffuser while the lower branch was stable. This hysteresis has been observed experimentally. The theory indicates that for a ram-jet engine of given diameter, the amplitude of pulsation of a supersonic diffuser is increased by decreasing the relative size of the plenum chamber with respect to the diffuser volume down to a critical value at which oscillations cease. In the region of these critical values, the stable mass-flow range of the diffuser may be increased either by decreasing the combustion chamber volume or by increasing the length of the diffuser.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E52I24
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  • 24
    Publication Date: 2019-07-12
    Description: The possibility of overshooting the anticipated normal acceleration as a result of the artificial-feel characteristics of the F-89C airplane at a condition of minimum static stability was investigated analytically by means of an electronic simulator. Several methods of improving the stick-force characteristics were studied. It is shown that, due to the lag in build-up of the portion of the stick force introduced by the bobweight, it would be possible for excessive overshoots of normal acceleration to occur in abrupt maneuvers with reasonable assumed control movements. The addition of a transient stick force proportional to pitching acceleration (which leads the normal acceleration) to prevent this occurring would not be practical due to the introduction of an oscillatory mode to the stick-position response. A device to introduce a viscous damping force would Improve the stick-force characteristics so that normal acceleration overshoots would not be likely, and the variation of the maximum stick force in rapid pulse-type maneuvers with duration of the maneuver then would have a favorable trend.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SA52L31
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  • 25
    Publication Date: 2019-07-12
    Description: An investigation was conducted in the Ames 12-foot pressure wind tunnel to determine the effect of an operating propeller on the aerodynamic characteristics of a l/l9-scale model of the Lockheed XFV-1 airplane, Several full-scale power conditions were simulated at Mach numbers from 0.50 to 0.92; the.Reynolds number was constant at 1,7 million. Lift, longitudinal force, pitch, roll, and yaw characteristics, determined with and without power, are presented for the complete model and for various combinations of model components, Results of an investigation to determine the characteristics of the dual-rotating propeller used on the model are given also,
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SA52E06
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  • 26
    Publication Date: 2019-07-12
    Description: The stator-blade angles in the first four stages of a 16-stage axial-flow compressor were increased in order to decrease the angles of attack of these stages, and thereby to improve part-speed performance. The performance of this modified compressor was compared with that of the same compressor with original blade angles.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E52B15
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  • 27
    Publication Date: 2019-07-12
    Description: An investigation of the effect of inlet pressure, corrected engine speed, and turbine temperature level on turbine-inlet gas temperature distributions was conducted on a J40-WE-6, interim J40-WE-6, and prototype J40-WE-8 turbojet engine in the altitude wind tunnel at the NAC.4 Lewis laboratory. The engines were investigated over a range of simulated pressure altitudes from 15,000 to 55,000 feet, flight Mach numbers from 0.12 to 0.64, and corrected engine speeds from 7198 to 8026 rpm, The gas temperature distribution at the turbine of the three engines over the range of operating conditions investigated was considered satisfactory from the standpoint of desired temperature distribution with one exception - the distribution for the J40-WE-6 engine indicated a trend with decreasing engine-inlet pressure for the temperature to exceed the desired in the region of the blade hub. Installation of a compressor-outlet mixer vane assembly remedied this undesirable temperature distribution, The experimental data have shown that turbine-inlet temperature distributions are influenced in the expected manner by changes in compressor-outlet pressure or mass-flow distribution and by changes in combustor hole-area distribution. The similarity between turbine-inlet and turbine-outlet temperature distribution indicated only a small shift in temperature distribution imposed by the turbine rotors. The attainable jet thrusts of the three engines were influenced in different degrees and directions by changes in temperature distributions with change in engine-inlet pressure. Inability to match the desired temperature distribution resulted, for the J40-WE-6 engine, in an 11-percent thrust loss based on an average turbine-inlet temperature of 1500 F at an engine-inlet pressure of 500 pounds per square foot absolute. Departure from the desired temperature distribution in the Slade tip region results, for the prototype J40-WE-8 engine, in an attainable thrust increase of 3 to 4 percent as compared with that obtained if tip-region temperature limitations were observed.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E52H06
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  • 28
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    Weinheim : Wiley-Blackwell
    Chemie Ingenieur Technik - CIT 24 (1952) 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
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  • 29
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 1-2 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Es wird ein Verfahren beschrieben, die wirksame Oberfläche eines Katalysators ohne Behinderung des Gastransportes zu erhöhen durch Aufbringen des katalysierenden Stoffes in Pulverform auf impräginerte Körner ohne Beimischung eines Bindemittels und ohne mechanischen Druck. Die Katalysatoren sind schüttfest. Sechs Beispiele mit vergleichenden Versuchen an großtechnisch wichtigen Prozessen zeigen eine um ein Vielfaches erhöhte Ausbeute.
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    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Das Aufzeigen der Merkmale im Aufbau von Zerstäubungstrocknern führt zu einer Betrachtung der Abmessungen der Teilchen, aus denen das Trockenpulver besteht. Mikroaufnahmen lassen die verschiedenen Einflüsse auf die Teilchengröße erkennen. Letztere legt ihreseits die Größe der Wärmeund Stoffaustauschzahlen fest. Das Hauptergebnis dieser theoretischen Untersuchungen ist die Trockenzeit. Je nach Teilchenabmessung schwankt sie zwischen Bruchteilen und einer Vielzahl von Sekunden. Auch der Betriebsmittelverbrauch wird untersucht; es wird gezeigt, wie der Wärmeverbrauch erniedrigt werden kann.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 22-25 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: In den bis jetzt in der amerikanischen Literatur veröffentlichten beiden Enthalpie - Diagrammen wird nicht das metrische Maßsystem angewendet oder sie umfassen nicht das ganze Gebiet des Systems Wasser-Schwefelsäure-Schwefeltrioxyd. Außerdem ist die Genauigkeit der Enthalpiewerte schwer zu beurteilen, da die Verfasser die Auswertung der experimentellen Daten nicht erklären. Im folgenden wird nun über die Berechnung und Konstruktion eines Enthalpie-Diagramms im metrischen Maßsystem über das gesamte Gebiet des Systems ausführlich berichtet, und Fehlergrenzen werden angegeben.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 32-36 
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    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 36-41 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
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    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Es wird über die Arbeiten dreier Autoren berichtet, die möglichst einfache Formen der Dispersoidanalyse für technische Zwecke entwickelt haben. Zwei Arbeiten befassen sich mit der Verbesserung oder Vereinfachung bekannter Methoden, die auf der Sedimentation von Dispersoiden in Flüssigkeiten bzw. der Messung der Durchlässigkeit des aufgehäuften Materials beruhen. Die dritte Arbeit benutzt die Dispersion des Lichts in Abhängigkeit von der Teilchengröße, den sog. Mie-Effekt, und verspricht bei Einsatz entsprechender optischer Mittel eine fast augenblickliche Messung, die auch die Bildung oder Veränderung von Dispersionen zu verfolgen gestatten würde.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 41-42 
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    Keywords: Chemistry ; Industrial Chemistry
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 42-44 
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    Keywords: Chemistry ; Industrial Chemistry
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 45-46 
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    Keywords: Chemistry ; Industrial Chemistry
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 47-49 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 49-50 
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    Keywords: Chemistry ; Industrial Chemistry
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 58-59 
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    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 60-81 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Es wird an Hand von Photographien ein Überblick über das Verhalten von mit Gasen oder Flüssigkeiten aufgeströmten, gekörnten Schüttgütern gegeben. Auf Grund der vorliegenden Literatur und eigener Arbeiten werden quantitative Angaben gemacht über die Größe des Druckabfalles in Wirbelschichten, die minimalen und maximalen Geschwindigkeiten, bei denen eine Wirbelschicht noch beständig ist, und über die Schichtausdehnung infolge der Wirbelbewegung des gekörnten Gutes. Weitere Angaben folgen über die Viscosität in Wirbelschichten, den Böschungswinkel sowie den Stoff- und Wärmetransport, den Abrieb des wirbelnden Kornmaterials, die Erosion der Apparatewände sowie über chemische Umsetzungen in Wirbelschichten.
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    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Notes: In der vorliegenden Arbeit werden Aufströmungseigenschaften und hydrodynamische Zustände mit Luft aufgewirbelter Partikelschichten untersucht. Anschliεßend wird eine Versuchsanordnung und Methode für Wärmeübergangs-Messungen in solchen Schichten im Vergleich zu ruhenden Schüttungen behandelt und eine Deutung der Versuchsergebnisse gegeben.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 92-92 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Notes: Es wird die Formulierung des Winkler-Verfahrens in deutschen und amerikanischen Patentschriften erörtert, wobei wesentlich ist, daß die Vergasung in einer bewegten Schicht stattfindet.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 93-97 
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    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Notes: Eine Schicht von losem, feinkörnigem Schüttgut läßt sich in einem Behälter durch eine richtig dosierte Gasströmung in einen beweglichen Zustand versetzen. Die Schicht verhält sich dann ähnlich wie eine Flüssigkeit. Es werden Untersuchungen und Verfahren beschrieben, denen das Prinzip der Wirbelschicht zugrunde liegt.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 110-114 
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    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 129-135 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Notes: Aus dem bei der Badischen Anilin-& Soda-Fabrik, Ludwigshafen, entwickelten Spiralwindsichter entstand durch die Einführung rotierender Sichtraumwände, einer sich automatisch der Trenngrenze anpassenden Grobgutspülung und nach sorgfältiger konstruktiver Durcharbeitung eine betriebsreife Maschine. Bei dieser Entwicklung wurden neue Erkenntnisse über die Definition der Korngröße und das Ansatzverhalten von Feinstäuben gewonnen. Die vermutliche Weiterentwicklung wird abschließend skizziert.
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    ISSN: 0009-286X
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    Notes: Den zahlreichen Vorschlägen zur wirtschaftlichen Bewertung von Wärmeübertragern wird die Anregung entgegengestellt, die Kosten für den Gesamtaufwand an Rohrlänge zur wichtigsten Grundlage einer wirtschaftlichen Bewertung verschiedener Gestaltungen zu machen. Die Vergleiche werden für Längsstrom in Rohren und für Querstrom durch Rohrbündel mit Einschluß berippter Rohre in einheitlicher und systematischer Weise durchgeführt. Besonders bei niedrigen Re-Zahlen erweisen sich Querstrom-Anordnungen mit engen Rohrabständen als wirtschaftlich überlegen.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 156-157 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Um die Betriebssicherheit und Lebensdauer von Vakuumpumpen zu erhöhen, kann ein Staubfilter vorgeschaltet werden. Hierfür lassen sich ein U-Rohrfilter bzw. ein Öl-Umlauffilter, die mit trockenen bzw. ölbenetzten Raschig-Ringen gefüllt sind, verwenden.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 160-163 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 165-165 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 158-159 
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    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Bei der Auswertung photographisch aufgenommener Spektren sowie der intensitätsmäßigen Auswertung von Röntgenaufnahmen, speziell von Faseraufnahmen und diffusen Streukurven, muß man die vom Registrierphotometer gelieferte Kurve auf Intensität bzw. Schwärzung umwerten. Es wird ein aus einfachen Mitteln herstellbarer Apparat angegeben, der dies mechanisch ausführt und sich gut bewährt hat.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 163-165 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 166-168 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 169-169 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 169-170 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 171-172 
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    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Berichtet wird über wesentliche Fortschritte der Fischer-Tropsch-Synthese mit festangeordnetem Katalysator. Die Entwicklung hochaktiver Eisen-Katalysatoren und Aufklärung wichtiger Fragen der Reaktionskinetik und des Wärmetransportes in den Reaktoren ermöglichte erhebliche Erhöhung der Ausbeute und Qualität der Produkte und technische Verbesserung der Synthese-Anlagen, so daß die Wirtschaftlichkeit des Fischer-Tropsch-Prozesses unter sehr verschiedenartigen Bedingungen gegeben ist. Erstmalig werden zusammenfassende Mitteilungen über die Qualität der aus diesen Produkten von der Ruhrchemie großtechnisch hergestellten synthetischen Schmieröle gemacht.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 262-271 
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    Notes: Die Schwingungstechnik hat in den letzten Jahren auch in der chemischen Industrie ständig an Bedeutung gewonnen. Einmal ergaben sich in vorhandenen Anlagen bei Erweiterungen Schwierigkeiten, so daß man auf neue Erkenntnisse der Schwingungstechnik angewiesen war, zum anderen aber wollte man auch bei Neuplanungen die Vorteile schwingungstechnischer Gründung von Maschinen von vornherein ausnutzen. Im folgenden wird eine Übersicht gegeben über die sich bietenden Probleme und deren praktische Lösungen, wie sie mit Erfolg bereits verwirklicht sind oder z. Zt. verwirklicht werden.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 272-277 
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    Notes: Im folgenden werden die Grundzüge der Physik der Festkörper, soweit sie zum Verständnis der Pulverdispersoide notwendig sind, behandelt. Der Einfluß von mechanischem Zerkleinerungsgrad, Eigengewicht, Kristallstruktur und -oberfläche auf das Verhalten von Pulvern wird dargelegt.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 277-283 
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    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Am Beispiel des Penicillin wird die großtechnische Herstellung der Antibiotika behandelt. Besonderheiten, die sich für die Reinigung von Streptomycin und Aureomycin aus ihren chemischen Eigenschaften ergeben, werden berücksichtigt.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 284-288 
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    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Zur Untersuchung von Sedimentations-, Elektrophorese- und Diffusionsvorgängen wurde ein lichtstarkes Meßverfahren nach der Interferenzmethode entwickelt, das den Vorteil der hohen Lichtstärke einer Jaminschen Anordnung des Planparallelplatten - Interferometers gegenüber dem Doppelspalt-Interferometer voll ausnutzt, indem als optisches Zusatzglied zwei gewinkelte gleichdicke Planparallelplatten angefügt werden. Ein Gerät zur Messung der Diffusionskonstanten wird beschrieben.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 326-327 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 317-320 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 327-328 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 321-325 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 333-338 
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    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: In der Verfahrenstechnik spielen rheologische Einflüsse eine bedeutende Rolle. An Beispielen aus der Reyon- und Zellwollindustrie wird gezeigt, daß u. a. die Spinnlösung in den verschiedenen verfahrenstechnischen Stufen ein unterschiedliches Verhalten aufweist. Durch eine rheologische Betriebskontrolle können der Fabrikationsprozeß überwacht und Aussagen über die Qualität des Ausgangsproduktes und der Fertigprodukte gemacht werden.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 339-347 
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    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: An Hand einiger Beispiele der Praxis wird Stellung genommen zur Frage, welche Faktoren bei bestimmten, mit etwa atmosphärischen Drucken betriebenen Gaserzeugertypen die Zusammensetzung der Vergasungsgase beeinflussen.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 349-352 
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    Notes: Auf Grund neuerer experimenteller Ergebnisse englischer und russischer Autoren werden unter Heranziehung eigener reaktionskinetischer Untersuchungen die vermutlichen Elementarreaktionen der aus den Experimenten folgenden drei Reaktionsstufen der Kohleverbrennung Cfest + ½ O2 = CO; CO + ½ O2 = CO2; CO2 + Cfest = 2 CO aufgestellt. Es wird versucht, aus dem Elementarablauf die experimentellen Befunde abzuleiten und verständlich zu machen. Die Vorgänge bei der Vergasung der Kohle sowie Fragen der Energieverteilung zwischen Festkörper und Gas werden diskutiert.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 348-348 
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    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Es wird ein Ofen beschrieben, der zum Ausglühen von Kupferoxyd für die Stickstoff-Bestimmung nach Dumas gebraucht wird, sich aber auch zum Ausglühen von körnigen Substanzen in beliebigem Gasstrom eignet.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 359-364 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 373-373 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 364-373 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 353-357 
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    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: An Hand einer umfangreichen Tabelle wird gezeigt, daß sich das Guldbergsche Verhältnis ϑ = Ts/Tk für organische Verbindungen additiv aus Atom- und Gruppenwerten zusammensetzen läßt. Damit wird es möglich, die absolute kritische Temperatur Tk eines organischen Stoffes abzuschätzen, wenn dessen Siedetemperatur Ts bekannt ist.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 373-376 
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    Notes: Es wird ein lösbarer Hochdruckverschluß beschrieben, bei dem die Abdichtung durch einen Kupferring bewirkt wird. Sodann wird der Kraftfluß durch den Kupferring ermittelt sowie die durch die Abdichtung bewirkte Biegespannung im Behälter.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 377-378 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 378-380 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 380-381 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 381-381 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 381-381 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 382-388 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 389-392 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 401-402 
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    Notes: Es wird gezeigt, daß die im Betriebe von Spinnbadeindampfern fallweise auftretenden, schwer entfernbaren Verkrustungen der Heizrohre im wesentlichen durch die Ausscheidung von Glauberit verursacht werden. Verschiedene Einflüsse, die die Bildung des Doppelsalzes begünstigen, werden aufgeklärt.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 403-404 
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    Notes: Durch Anwendung eines temperaturkompensierten Aräometers nach Neubauer wird eine sehr genaue und schnelle Gehaltsbestimmung rauchender Schwefelsäure möglich. Weitere Anwendungen des neuen Gerätes werden kurz erörtert.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 405-411 
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    Notes: Es werden behandelt die Abhängigkeit der Kolonnenbelastung vom Differenzdruck für verschiedene Füllkörper und verschiedene Einsatzprodukte, die Belastung bei vermindertem Druck, die Wirksamkeit verschiedener Füllkörper in Abhängigkeit von der Belastung und der günstigste Belastungsbereich.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 411-413 
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    Notes: Es wird über die Entwicklung im Bau von Hochdruckgefäßen, Verschlußvorrichtungen, Armaturen, Pumpen und Verdichtern sowie Meßgeräten berichtet.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 393-400 
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    Notes: An einer Universal-Versuchseinrichtung gewonnene neue Versuchsergebnisse werden zusammenfassend mitgeteilt. Sie betreffen das Kondensieren, Verdampfen, Erwärmen und Kühlen. Für kondensierenden Wasserdampt gestatten die Messungen einen Vergleich zwischen Theorie und Wirklichkeit einerseits und zwischen Film- sowie Tropfenkondensation andererseits. Enthält der Dampf Luft, dann ist für die Vorausberechung eine zweckentsprechende Deutung des hydraulischen Durchmessers unerläßlich. Für diese wird ein Beitrag geliefert. Die am senkrechten Versuchsrohr gemessenen Wandtemperaturen gestatten, die Wärmeübergangszahl zwischen Rohrwand und im Rohr wahlweise bei auf- und abwärts strömendem Wasser zu messen. Infolge Eigenkonvektion ergeben sich bei kleinen Geschwindigkeiten in beiden Fällen unerwartet hohe Unterschiede gegenüber den bekannten Gleichungen. Überraschend sind aber die jetzt erstmalig bekanntgegebenen Beobachtungen über den Einfluß des Schämens auf den Wärmeübergang im senkrechten Verdampferrohr. Das Schäumen erhöht den Wärmeübergang von Lösungen im selben Maß wie die Tropfenbildung beim Kondensieren von Wasserdampf.
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 414-415 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 415-419 
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    Chemie Ingenieur Technik - CIT 24 (1952), S. 420-420 
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