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  • Cell & Developmental Biology  (452)
  • Industrial Chemistry  (296)
  • Aircraft Design, Testing and Performance  (168)
  • AERODYNAMICS  (25)
  • 1945-1949  (941)
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  • 1
    Publication Date: 2019-06-28
    Description: The material given in this report summarizes some of the results of recent research that will aid the designers of an airplane in selecting or modifying a configuration to provide satisfactory stability and control characteristics. The requirements of the NACA for satisfactory flying qualities, which specify the important stability and control characteristics of an airplane from the pilot's standpoint, are used as the main topics of the report. A discussion is given of the reasons for the requirements, of the factors involved in obtaining satisfactory flying qualities, and of the methods used in predicting the stability and control characteristics of an airplane. The material is based on lecture notes for a training course for research workers engaged in airplane stability and control investigations.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TR-927
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  • 2
    Publication Date: 2019-06-28
    Description: An investigation has been conducted in the NACA Cleveland icing research tunnel to determine the aerodynamic and icing characteristics of several recessed fuel-vent configurations. The vents were investigated aerodynamically to obtain vent-tube pressures and pressure distributions on the ramp surface as functions of tunnel-air velocity and angle of attack. Icing investigations were made to determine the vent-tube pressure losses for several icing conditions at tunnel-air velocities ranging from 220 to 440 feet per second. In general, under nonicing conditions, the configurations with diverging ramp walls maintained, vent-tube pressures greater than the required marginal value of 2 inches of water positive pressure differential between the fuel cell and the compartment containing the fuel cell for a range of angles of attack from 0 to 14deg at a tunnel-air velocity of approximately 240 feet per second. A configuration haying divergIng ramp sldewalls, a 7deg ramp angle; and vent tubes manifold,ed to a common plenum chamber opening through a slot In the ramp floor gave the greatest vent-tube pressures for all the configurations investigated. The use of the plenum chamber resulted in uniform pressures in all vent tubes. In a cloud-icing condition, roughness caused by ice formations on the airfoil surface ahead of the vent ramp, rather than icing of the vent configuration, caused a rapid loss in vent-tube pressures during the first few minutes of an icing period. Only the configuration having diverging ramp sidewalls, a 7 ramp angle, and a common plenum chamber maintained the required vent-tube pressures throughout a 60-minute icing period, although the ice formations on this configuration were more severe than those observed for the other configurations. No complete closure of vent-tube openings occurred for the configurations investigated. A simulated freezing-rain condition caused a greater and more rapid vent-tube pressure loss than was observed for a cloud-icing condition.
    Keywords: AERODYNAMICS
    Type: NACA-TN-1789
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  • 3
    Publication Date: 2019-07-12
    Description: Wind tunnel tests of the 0.16-scale Douglas MX-656 model were made at low and high subsonic Mach numbers to investigate the static longitudinal- and lateral stability characteristics. The tests shows that undesirable changes in longitudinal stability at the stall were apparently caused by an altered downwash pattern at the tail. The jettisonable nose fins were highly destabilizing. Compressibility effects for the test Mach numbers were not detrimental to the longitudinal- or lateral-stability characteristics.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SA9D26
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  • 4
    Publication Date: 2019-07-12
    Description: Measurements of wing and fuselage pressure distributions were made at low and high subsonic Much numbers on a 0.16-scale model of the projected MX-656 research airplane. The MX-656 is a supersonic design utilizing a low-aspect-ratio wing and tail. Pressure-distribution measurements indicated that, although the critical Mach number of the wing was approximately 0.81 at 0 degree angle of attack, compressibility effects were of little significance below a Mach number of at least 0.90. The principal effect of compressibility was an increase in the pressure gradient over the after 30 percent of the wing chord, causing a tendency for the flow to separate. At 0.40 Mach number, the wing stalled abruptly at approximately 12 deg, angle of attack. The wing-pressure distribution showed this stall was a result of complete separation of the flow from the upper surface of the wing, Deflecting the leading-edge flaps delayed the stall to a higher angle of attack with some increase in the maximum section normal force,
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SA9H22
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  • 5
    Publication Date: 2019-07-11
    Description: The present report, which deals with pressure-distribution measurements made on a sweptback wing with a jet engine nacelle, is similar to a report on pressure-distribution measurements on a rectangular wing with a jet engine nacelle (second partial report). Here, in investigations preliminary to high-speed measurements, as in the second partial report, useful arrangements and fillet designs have been discovered.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1226 , ZWB Der Luftfshrtforschung des Generalluftzeugmeisters Berlin-Adlershof, Untersuchungen und Mitteilungen Nr. 3176; Rept-3176
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  • 6
    Publication Date: 2019-07-11
    Description: The present report, which forms the first of six articles on experiments with airfoils of aspect ratio from 1 to 3 and various planforms, deals with the three- and six-component measurements made on the trapezoidal wing series in the 2.15 x 3-meter wind tunnel of the DVL at the request of the Henschel Aircraft Company.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1225 , ZWB Luftfahrtforeschung des Generalluftzeugmeisters - Berlin-Adelerehof, Untersuchungen und Mitteilungen Nr. 1023/1; Rept 1023/1
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  • 7
    Publication Date: 2019-07-11
    Description: An investigation was conducted on an 0.08-scale semispan model of the Chance Vought XF7U-1 airplane in the Langley high-speed 7- by 10-foot tunnel in the Mach number range from 0.40 to 0.97. The results are compared with those obtained with an 0.08-scale sting-mounted complete model tested in the same tunnel and with an 0.026-scale semispan model tested by the wing-flow method. The lift-curve slopes obtained for the 0.08-scale semispan model and the 0.026-scale wing-flow model were in good agreement but both were generally lower than the values obtained for the sting model. The results of an unpublished investigation have shown that tunnel-wall boundary-layer and strut-leakage effects can came the difference noted between the lift-curve slopes of the sting and the semispan data. Fair agreement was obtained among the data of the three models as regard the variation of pitching-moment coefficients with lift coefficient. The agreement between the complete and the semispan models was more favorable with the vertical fine on, because the wall-boundary-layer and strut leakage effects were less severe. In the Mach number range between 0.94 and 0.97, ailavator-control reversal was indicated in the wing-flow data near zero lift; Whereas, these same trends were indicated in the larger scale semispan data at somewhat higher lift coefficients.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL9A13
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  • 8
    Publication Date: 2019-07-11
    Description: The present report is concerned with a series of tests on a model airplane fitted with four types of dive flaps of various shapes, positions, and incidence located near the leading edge of the wing (from 5 to 20 percent of the wing chord). Tests were also made on a stub airfoil fitted with a ventral dive (located at 8 percent of the wing chord). The hinge moments of the dive flaps were measured.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1161 , Relazione Tecnica No. 10: Ministereo dell' Aeronautica Direzione Superiore Studi ed Esperienze
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  • 9
    Publication Date: 2019-07-11
    Description: The flexural vibration of a rotating propeller blade with clamped shank is analyzed with the object of presenting, in matrix form, equations for the elastic bending moments in forced vibration resulting from aerodynamic forces applied at a fixed multiple of rotational speed. Matrix equations are also derived which define the critical speeds end mode shapes for any excitation order and the relation between critical speed and blade angle. Reference is given to standard works on the numerical solution of matrix equations of the forms derived. The use of a segmented blade as an approximation to a continuous blade provides a simple means for obtaining the matrix solution from the integral equation of equilibrium, so that, in the numerical application of the method presented, the several matrix arrays of the basic physical characteristics of the propeller blade are of simple form, end their simplicity is preserved until, with the solution in sight, numerical manipulations well-known in matrix algebra yield the desired critical speeds and mode shapes frame which the vibration at any operating condition may be synthesized. A close correspondence between the familiar Stodola method and the matrix method is pointed out, indicating that any features of novelty are characteristic not of the analytical procedure but only of the abbreviation, condensation, and efficient organization of the numerical procedure made possible by the use of classical matrix theory.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-8I07
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  • 10
    Publication Date: 2019-07-11
    Description: A model of a Consolidated Vultee Aircraft Corporation Skate 7 sea-plane:was tested in Langley tank no= 2. Resistance data, 'spray photographs, and underwater photographs,are given in this report without discussion.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL9G21
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  • 11
    Publication Date: 2019-07-11
    Description: A vane-type angle-of-attack indicator suitable for measurements at both subsonic and supersonic speeds has been developed by the National Advisory Committee for Aeronautics. A brief history is given of the development, and a wind-tunnel calibration of the indicator is presented, together with a discussion of the corrections to be applied to the indicated readings.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L9F28a
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  • 12
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    In:  CASI
    Publication Date: 2019-07-11
    Description: The purpose of the model tests is to clarify the motions in the alighting on water of a land plane. After discussion of the model laws, the test method and test procedure are described. The deceleration-time-diagrams of the landing of a model of the Bf 109 show a high deceleration peek of greater than 20g which can be lowered to 4 to 6g by radiator cowling and brake skid.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1247 , Wasserlandung Bf 109. Institut fuer Seeflugwesen er Deutschen Versuchaanstalt fuer Luftfahrt, E. V.
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  • 13
    Publication Date: 2019-07-11
    Description: Wind-tunnel tests of a full-scale model of the Republic XF-91 airplane were conducted to determine the distribution of pressure over the external wing fuel tank installation and over the vee tail and ventral fin. The data were obtained for a range of angles of attack and sideslip and elerudder deflection angles; the presentation is in tabular form.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SA9C25
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  • 14
    Publication Date: 2019-07-11
    Description: In order to obtain insight into the flow conditions on tail surfaces on airplanes during spins, pressure-distribution measurements were performed on a rotating model of the design BFW-M31. For the time being, the tests were made for only one angle of attack (alpha = 60 degrees) and various angles of yaw and rudder angles. The results of these measurements are given; the construction of the model, and the test arrangement used are described. Measurements to be performed later and alterations planned in the test arrangement are pointed out.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1220 , ZWB Forschungsbericht Nr. 704; Rept-704
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  • 15
    Publication Date: 2019-07-11
    Description: The effect of application of power, so far not clarified, is investigated in the present report in order to give the pilot, in addition to the control measures, an expedient for spin recovery of multiengine airplanes. To this end, a series of spins was performed with an airplane of the Go 150 type. It was possible to set up a uniform rule regarding the effect of power, for right end left spins as well as for any combination of the direction of rotation of the propellers.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1219 , ZWB Forschungsbericht Nr. 1536; Rept 1536
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  • 16
    Publication Date: 2019-07-11
    Description: Results of previous model ditching tests of the Lockheed Constellation airplane are reported. Further model tests have been made to determine the probable ditching characteristics and the proper ditching technique for the airplane with the Speedpak attached. This paper presents the results of these tests. Design information was furnished by the Lockheed Aircraft Corporation. A three-vies drawing of the airplane with the Speedpak attached is shown. The tests were made in calm water at the Langley tank no.2 monorail.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL9H05a
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  • 17
    Publication Date: 2019-07-11
    Description: Flight tests were conducted at the NACA Pilotless Aircraft Research Station, Wallops Island, to determine the characteristics of the Allegany Ballistics Laboratory's 6.2inch-diameter Deacon and lO-inch-scale model solid-propellant rocket motors. The tests were performed to assist in the development of these rockets which were designed for, and urgently needed to propel supersonic research models and pilotless aircraft. The tests showed that the rocket motors functioned properly under various flight- acceleration loads over a range of pre-ignition grain temperatures. A maximum velocity of 4180 feet per second was obtained at an elapsed time of 2.9 seconds with the 6.25-inch Deacon rocket motor at a gross weight of l9O pounds. Free-flight data of drag coefficient for the Deacon configuration for a Mach number range of 1.1 to 3.6 have been obtained from flight tests of several pounds. Camera studies of the take-off and flights of the Deacon rocket shared no evidence of breakup of propellant grains. An analysis of the forces to which the Deacon rocket grain is subjected was made. The analysis shows that the grain loading is most severe near the beginning and near the end of the rocket action time. The 10-inch-scale model rocket motor is a scaled model of the l6-inch- diameter multi-perforated, cast-grain rocket motor. A maximum velocity of 1625 feet per second at a time of 1.075 seconds was obtained at a gross weight of 309 pounds.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L8H26
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  • 18
    Publication Date: 2019-07-12
    Description: A spin-recovery investigation has been conducted in the Langley 20-foot free-spinning tunnel on a 20-scale model modified to represent the McDonnell XF2H-1 airplane. The project included tests both with tip tanks installed and with the tanks removed. The results indicated that the recovery characteristics of the airplane would be satisfactory for all loadings by normal recovery technique (full reversal of the rudder, followed 1/2 turn later by movement of the elevator down). The rudder pedal and the elevator stick forces likely to be encountered in a spin should be within the capabilities of the pilot.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL9F17
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  • 19
    Publication Date: 2019-07-12
    Description: Studies have been made by the NACA wing-flow method of the use of fuselage static orifices between the wing and tail of a swept-wing airplane for possible application to service airspeed installations. The tests were made at zero angle of attack. The results indicate that, although the maximum errors are large, these locations are usable from the consideration that the local Mach numbers at the locations studied are sensitive to variation of the true Mach number within the test Mach number range of 0.7 to 1.2. The maximum errors in Mach number in the subsonic range varied from zero for the most forward location to -0.05 for the most rearward location (indicated Mach number less than true). At Mach numbers above 1.0, the maximum errors were from 0.14 for the most forward location to 0.04 for the most rearward location.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL9J21
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  • 20
    Publication Date: 2019-07-12
    Description: The take-off stability characteristics of a Consolidated Vultee Aircraft Corporation Skate 7 seaplane were determined in the Langley tank no. 2. Trim limits of stability, trim tracks, and elevator limits of stability are presented.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL9D28a
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  • 21
    Publication Date: 2019-07-12
    Description: High-speed wind-tunnel tests were conducted of two versions of a 0.17-scale model of the McDonnell XF2H-1 airplane to ascertain the high-speed stability and control characteristics and to study means for raising the high-speed buffet limit of the airplane, The results for the revised model, employing a thinner wing and tail than the original model, revealed a mild diving tendency from 0.75 to 0.80 Mach number, followed by a marked climbing tendency from 0.80 to 0.875 Mach number. The high-speed climbing tendency was caused principally by the pitching-moment characteristics of the wing. At 0.875 Mach number the results for the revised model indicated stick-fixed directional instability over a limited range of yaw angles, apparently caused by separated flow over the vertical tail. The test results indicate that the high-speed buffet limit of the airplane can probably be raised by reducing the thickness and changing the relative location of the horizontal and vertical tails, and by revising the inner portion of the wing to have a lower thickness-to-chord ratio and reduced trailing-edge angle. The addition of the wing-tip tanks to the revised model resulted in a forward shift in the neutral point below 0.82 Mach number.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SA9C31
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  • 22
    Publication Date: 2019-07-12
    Description: An investigation was conducted to determine the longitudinal- and lateral-stability characteristics of a 0.5-scale moue1 of the Fairchild Lark missile, The model was tested with 0 deg and with 22.5 deg of roll. Three horizontal wings having NACA 16-009, 16-209, and 64A-209 sections were tested. Pressures were measured on both pointed and blunt noses. The wind-tunnel-test data indicate that rolling the missile 22.5 deg. had no serious effect on the static longitudinal stability. The desired maneuvering acceleration could not be attained with any of the horizontal wings tested, even with the horizontal wing flaps deflected 50 deg. The flaps on the 64A-209 wing (with small trailing-edge angles and flat sides) were effective at all flap deflections, while the flaps on the 16-series wings (with large trailing-edge angles) lost effectiveness at small flap deflections. The data showed that rolling moment existed when the vertical wing flaps were deflected with the model at other than zero angle of attack. A similar rolling moment probably would be found . with the horizontal wing flaps deflected and the model yawed.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SA9I28 , NACA DE322
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  • 23
    Publication Date: 2019-07-12
    Description: An investigation has been conducted with the Langley helicopter tower to obtain basic performance and control characteristics of the Raman rotor system. Blade-pitch control is obtained in this configuration by utilizing an auxiliary flap to twist the blades. Rotor thrust and power required were measured for the hovering condition and over a range of wind velocities from 0 to 30 miles per hour. The control characteristics and the transient response of the rotor to various control movements were also measured. The hovering-performance data are presented as a survey of the wake velocities and the variation of torque coefficient with thrust coefficient. The power required for the test rotor to hover at a thrust of 1350 pounds and a rotor speed of 240 rpm is approximately 6.5 percent greater than that estimated for a conventional rotor of the same diameter and solidity. It is believed that most of this difference is caused by th e flap servomechanism. The reduction in total power required for sustentation of the single-rotor configuration tested at various wind velocities and at the normal operating rotor thrust was found to be similar to the theoretical and experimental results for ro tors with conventionally actuated pitch. The control effectiveness was determined as a function of rotor speed. Sufficient control was available to give a thrust range of 0 to 1500 pounds and a rotor tilt of plus or minus 7 degrees. The time lag between flap motion and blade-pitch response is approximately 0.02 to 0.03 second. The response of the rotor following the blade-pitch response is similar to that of a rotor with conventionally actuated pitch changes. The over-all characteristics of the rotor investigated indicate that satisfactory performance and control characteristics were obtained.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL9I27
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  • 24
    Publication Date: 2019-07-12
    Description: An investigation was made to evaluate the hydrodynamic qualities of a 0.425-scale model of the Navy XP5M-1 hull, which was installed on a modified Navy J4F-2 amphibian. Longitudinal and directional stability during take-off and landing, low-speed maneuverability, spray characteristics, and take-off performance were investigated. The behavior of the airplane in moderately rough water was also observed. The opinions of three pilots have been correlated with the data.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL9L07a
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  • 25
    Publication Date: 2019-07-12
    Description: A flight test of the Aero jet Engineering Corporation's 7KS-6000 T-27 Jato rocket motor was conducted at the Langley Pilotless Aircraft Research Station at Wallops Island, Va, to determine the flight performance characteristics of the motor. The flight test imposed an absolute longitudinal acceleration of 9.8 g upon the rocket motor at 2.8 seconds after launching. The total impulse developed by the motor was 43,400 pound-seconds, and the thrusting time was 7.58 seconds. The maximum thrust was 7200 pounds and occurred at 4.8 seconds after launching. No thrust irregularities attributable to effects of the flight longitudinal acceleration were observed. Certain small thrust irregularities occurred in the flight test which appear to correspond to irregularities observed in static tests conducted elsewhere. A hypothesis regarding the origin of these small irregularities is presented.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL9L13a
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  • 26
    Publication Date: 2019-08-15
    Description: A preliminary analysis of the flying qualities of the Consolidated Vultee MX-813 delta-wing airplane configuration has been made based on the results obtained from the first two 1/8 scale models flown at the NACA Pilotless Aircraft Research Station, Wallop's Island, VA. The Mach number range covered in the tests was from 0.9 to 1.2. The analysis indicates adequate elevator control for trim in level flight over the speed range investigated. Through the transonic range there is a mild trim change with a slight tucking-under tendency. The elevator control effectiveness in the supersonic range is reduced to about one-half the subsonic value although sufficient control for maneuvering is available as indicated by the fact that 10 deg elevator deflection produced 5g acceleration at Mach number of 1.2 at 40,000 feet.The elevator control forces are high and indicate the power required of the boost system. The damping. of the short-period oscillation is adequate at sea-level but is reduced at 40,000 feet. The directional stability appears adequate for the speed range and angles of attack covered.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-Sl9E13
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  • 27
    Publication Date: 2019-07-12
    Description: Wind-tunnel tests at low Mach number of a Republic F-84C airplane were conducted to determine by pressure-distribution measurements the air loads on wing-tip tanks and the change in wing load distribution due to the presence of tip tanks. Measurements of the aeroelastic twist of the wing were also obtained. Results are presented in the form of loading coefficient, center-of- pressure location, pitching-moment coefficient, aerodynamic-center location, and aeroelastic twist. The investigation revealed that the redistributions in loading brought about by either the tip tanks or elastic deformation of the wing were relatively small when compared with the chnnges in loading normally associated with the deflection of an aileron.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SA9B02
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  • 28
    Publication Date: 2019-07-12
    Description: An additional series of high-speed wind-tunnel tests of a modified 0.17-scale model of the McDonnell XF2H-1 airplane was conducted to evaluate the effects of a reduction in the thickness-to-chord ratios of the tail planes, the displacement of the horizontal tail relative to the vertical tail, and the extension of the trailing edge of the wing. Two tail-intersection fairings designed to improve the flow at the tail were also tested. The pitching-moment characteristics of the model were improved slightly by the use of the thinner tail sections. Rearward or rearward and downward displacements of the horizontal tail increased the critical Mach number at the tail intersection from 0.725 to a maximum of 0.80, but caused an excessive change in pitching-moment coefficient at the higher Mach numbers. Extending the trailing edge of the wing did not improve the static longitudinal-stability characteristics, but increased the pitching-down tendency between 0.725 and 0.825 Mach numbers prior to the pitching-up tendency. The extended wing did, however, increase the Mach numbers at which these tendencies occurred. The increase in the Mach numbers of divergence and the tuft studies indicate a probable increase in the buffet limit of the prototype airplane. No perceptible improvement of flow at the tail intersection was observed with the two fairings tested on the forward tail configuration.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SA9J14
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  • 29
    Electronic Resource
    Electronic Resource
    Weinheim : Wiley-Blackwell
    Chemie Ingenieur Technik - CIT 21 (1949) 
    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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  • 30
    Electronic Resource
    Electronic Resource
    Weinheim : Wiley-Blackwell
    Chemie Ingenieur Technik - CIT 21 (1949), S. 6-8 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Die Anordnung dient zur Messung von Dampfdruckerniedrigungen verdünnter Lösungen (10-3 Mol/l) insbesondere assoziierender Substanzen. Es wurde eine Meßanordnung entwickelt, in der die durch kleine Druckdifferenzen verursachte Ausbuchtung der Wölbung des Meniskus eines Hg-Manometers nach dem Prinzip eines Photometers lichtelektrisch mit einem Vakuumthermoelement gemessen wird. Die Anordnung gestattet unabhängig vom Gesamtdruck noch Druckschwankungen von 10-4 mm Hg zu messen.
    Additional Material: 4 Ill.
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  • 31
    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 werden einige Regeleinrichtungen besprochen, die zum Aufbau von im wesentlichen automatisch arbeitenden Destillationskolonnen sowohl für diskontinuierlichen als auch für kontinuierlichen Betrieb führten.
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  • 32
    Electronic Resource
    Electronic Resource
    Weinheim : Wiley-Blackwell
    Chemie Ingenieur Technik - CIT 21 (1949), S. 1-6 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Unsere wichtigsten chemischen Großsynthesen gehen von Acetylen bzw. vom Kohlenoxyd-Wasserstoff-Gemisch aus. Die Arbeiten im letzten Jahrzehnt bezweckten, diese Rohstoffe unmittelbar aus dem Ferngas zu gewinnen. Von den entwickelten Verfahren verdient insbesondere das Sauerstoff-Verfahren Beachtung. Es liefert ein Synthesegas mit nur noch 0,2% Methan und ist unempfindlich gegen den im Ferngas vorhandenen organischen Schwefel. Eine etwa folgende Umsetzung des Kohlenoxydes mit Wasserdampf zu CO2 und Wasserstoff kann in unmittelbarem Ánschluß an der Kohlenwasserstoff-Spaltung vorgenommen werden, so daß kein neuer Dampfverbrauch auftritt. Während in der folgenden Arbeit über das Verfahren zur Verarbeitung des gesamten Ferngases auf Kohlenoxyd und Wasserstoff berichtet wird, wird in einer weiteren Arbeit die chemische Verwertung der einzelnen Bestandteile des Ferngases behandelt.
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  • 33
    Electronic Resource
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    Weinheim : Wiley-Blackwell
    Chemie Ingenieur Technik - CIT 21 (1949), S. 19-24 
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    Notes: Nach den verfügbaren amerikanischen Quellen wird zusammenfassend über die seit etwa 1940 in Amerika erreichten Fortschritte auf dem Gebiet der Sauerstoff-Erzeugung und -Anwendung berichtet, besonders über Versuche an Austauschböden und Trennkolonnen für kleinere, meist leichtbewegliche Anlagen, über die Mittel zur Kälteerzeugung, über die Herstellung und den Versand von flüssigem Sauerstoff sowie über die unmittelbare Erzeugung von hochkomprimiertem Sauerstoff für die Flaschenfüllung durch Verdampfung des flüssigen Sauerstoffs im Zerlegungsapparat. Weiter wird ein neuer Austauschertyp besprochen und auf neu erschlossene Anwendungsgebiete für billigen, mäßig reinen Sauerstoff hingewiesen.
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    Notes: Bei Kohlenoxyd-Hydrierungen unter Drucken zwischen 300 und 1000 at und Temperaturen über 400° erwiesen sich z. T. sog. „kohlenoxydfeste“ metallische Werkstoffe, insbesondere Stähle mit mehr als 13% Chrom, für den praktischen Betrieb als ungeeignet, obwohl sie anscheinend von Kohlenoxyd nicht abgebaut wurden. Es wurden daher 20 derartige Stähle und 6 eisenfreie Metallproben gegenüber Wassergas bei 1000 at und Temperaturen zwischen 300 und 450° untersucht und aus den Ergebnissen Folgerungen für die praktische Verwendungsmöglichkeit im Apparafebau gezogen.
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    Notes: Die Angabe, daß sich die Ausscheidung von Härtebildern mit Orthophosphaten in wässeriger Lösung unter Bildung von Tricalciumphosphat vollziehe, ist unzutreffend. Der Niederschlag dürfte vielmehr die Formel des Hydroxylapatits haben.
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    Notes: Bis 1940 war die Anwendung hoher Vakua fast nur auf das Laboratorium beschränkt, in der Technik evakuierte nur die Röhrenindustrie bis auf Drucke von beinahe 10-7 mm Hg, aber es handelte sich auch hier meist nur um verhältnismäßig kleine Volumina. Die anschließende Entwicklung wurde durch mehrere Ereignisse besonders gefördert: durch die Konstruktion hervorragender Pumpen in Deutschland und Amerika, durch die Schaffung guter Gläser in Jena, durch die Erfolge der Vakuumdestillation von Fetten, Ölen und empfindlichen organischen Substanzen in England, Deutschland und später in USA, und schließlich durch das amerikanische Atombombenprojekt, wo bereits bei der Gasdiffusions- und elektromagnetischen Trennung der Uran-Isotope die ersten großen Vakuum-Probleme auftraten. Heute ist selbst die großtechnische Erzeugung von Hochvakuum zwischen -100° und + 1000° C ein untergeordnetes Problem der Verfahrenstechnik geworden.
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    Notes: Es wird über Versuche mit zwei Ausführungen von Pilzglocken aus Porzellan berichtet, die in Rektifizierböden eingebaut waren. Wirkung, Druckverlust und Flüssigkeitsinhalt der Sälen wurden ermittelt. Um eine gute Wirkung zu erreichen, müssen die Einzelabmessungen des Bodens entsprechend gewählt werden. Auch der Einbau einer Staurippe erhöht die Bodenwirkung.
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    Notes: Die hier beschriebenen Methoden sollen es dem Schichtarbeiter mit einfachen Mitteln ermöglichen, kurzfristig eine gefährliche Acetylen-Anreicherung zu erkennen. Die Ergebnisse werden mit denen quantitativer Methoden verglichen.
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    Notes: Der im folgenden beschriebene Kolbenverdichter arbeitet mit ungeschmierten Kolben und Stopfbüchsen. Die Abdichtung wird durch Labyrinthdichtungen erreicht. Dadurch behält das verdichtete Medium die ursprüngliche Reinheit, so daß der Verdichter in der chemischen Industrie und der Lebensmittelindustrie da verwendet werden kann, wo völlig reine Druckluft gebraucht wird.
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    Notes: In den letzten Jahren hat die Fluorchemie, insbesondere die verschiedener organischer fluorierter Verbindungen, erheblich an praktischer Bedeutung gewonnen. Da in einigen Veröffentlichungenz. B. DECHEMA-Werkstofftabellen 1948; ferner Ind. Engng. Chem. 39, 12a u. 91a [1947]. bereits auf die gute Eignung des Silbers als Apparatebauwerkstoff für technische Reaktionen mit Fluorverbindungen hingewiesen worden ist, seien nachstehend einige quantitative Angaben gemasht, die das Ergebnis einer 1944 laboratoriumsmäßig durchgeführten Korrosionsprüfung darsfellen.
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    Notes: Die technisch-wissenschaftliche Forschung der letzten Jahrzehnte brachte eine Erweiterung und Vertiefung unserer Erkenntnisse über die beim gekoppelten Wärme- und Stoffaustausch sich abspielenden Vorgänge. Trotzdem blieben noch Fragen ungeklärt, deren erschöpfende Behandlung für die rechnerische Erfassung baispielsweise der Trocknungsvorgänge unerläßlich ist. Zu diesen Fragen gehört der Zusammenhang zwischen Luftzustand und Gutstemperatur während des Trocknens bei bestimmten Arten der Gasströmung. Im folgenden werden diese Verhältnisse untersucht, wobei sich eine gute Übereinstimmung zwischen theoretischen und experimentellen Ergebnissen ergibt.
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    Notes: Die bisherigen Definitionen des Wirkungsgrades von Wärmeaustauschern konnten zwangsläufig nicht in jeder Hinsicht befriedigen. Es wird auch immer schwierig sein, einen Wirkungsgrabegriff auf energetischer Grundlage aufzustellen, solange der Wärmeaustauschapparat allein betrachtet wird, da sich Wärme- und Druckverluste jeweils verschieden auswirken. Daher sollte auch das Arbeitsverfahren, in das der Wärmeaustauscher eingeschaltet ist, mit in Betracht gezogen werden. Im folgenden wird gezeigt, daß sich dann ein auf energetischer Grundlage beruhender Gütegradbegriff schaffen läßt, der zwar von Fall zu Fall neu aufgestellt werden muß, dafür aber eine Reihe von Vorteilen für den Erzeuger und den Abnehmer von Wäreaustauschapparaten bietet.
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    Notes: Der Auslaufbecher DIN 53211 ist ein einfaches, praktisch leicht zu handhabendes Betriebs-Gerät zur Beurteilung der Konsistenz besonders von Farben und Lacken. Die vorliegende Untersuchung zeigt, innerhalb welcher Grenzen der Auslaufbecher tatsächlich geeignet ist, ein zuverlässiges Maß für die Konsistenz mit ihren Nebenerscheinungen, z. B. für die Viskosität usw., zu sein. Der experimentelle Zusammenhang zwischen Auslaufzeit und Viskosität wird durch Versuche mit 11 Normalflüssigkeiten ermittelt. Die genaue Analyse der Versuchsergebnisse gibt einen interessanten Einblick in die Strömungsvorgänge bei diesem Gerät.
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 100-102 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Die Aufzeichnung polarographischer Kurven in Tintenschrift gestattet einfachstes Modellieren und Auswerten der Kurven. Für den Betrieb normaler Tintenschreiber unter Verstärkung der Elektrodenströme mittels Verstärker in Saugschaltung1 wurde während des Krieges ein vollelektrisch arbeitendes Zusatzgerät durchgebildet, in dem alle erforderlichen Schaltelemente und Verstellorgane zur Kurvenaufnahme untergebracht sind. Die einfach zu bedienende, robuste und universell verwendbare polarographische Meßeinrichtung läßt sich auch in technischen Betrieben zur Durchführung von Serienanalysen verwenden. Seine Wirkungsweise wird im folgenden unter Beifügung einiger charakteristischer Kurven erläutert.
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 110-114 
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 106-110 
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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: Vielen Betrieben steht Kühlwasser zur Verfügung, das reich an Carbonathärte ist und daher leicht Versteinungen der Leitungen hervorruft. Um diese Steinbildung zu verhindern, hat sich der Zusatz geringer Mengen an Natriumhexametaphosphat bewährt. Während man zur Prüfung der Brauchbarkeit von Zusätzen bisher einfache Becherglasversuche angestellt hat, haben die Verfasser ein geeignetes, im Laboratorium durchführbares Prüfverfahren entwickelt, wobei die wesentlichen betrieblichen Faktoren berücksichtigt werden können. Im folgenden wird diese Apparatur beschrieben und dann werden damit erzielte Versuchsergebnisse mitgeteilt, die mit den in der Praxis gemachten Erfahrungen gut übereinstimmen. In einem Anhang wird schließlich über Becherglasversuche mit organischen Zusätzen berichtet.
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 116-116 
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    Keywords: Chemistry ; Industrial Chemistry
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