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  • Chemistry  (3,659)
  • Inorganic Chemistry  (578)
  • Polymer and Materials Science  (440)
  • Aircraft Design, Testing and Performance  (168)
  • Fluid Mechanics and Thermodynamics  (44)
  • Temperatur  (17)
  • LUNAR AND PLANETARY EXPLORATION
  • 1945-1949  (3,888)
Collection
Keywords
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Years
Year
  • 1
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    In:  Zeitschrift für Pflanzenernährung, Düngung, Bodenkunde 46:176-190
    Publication Date: 1949
    Description: Zusammenhang zwischen Witterungsverlauf, Wasserbedarf und Erträgen, Aufstellung einer Konstitutionstheorie KATASTER-BESCHREIBUNG: Anpassung an den Wassermangel in der Jugend, Erziehung zur Dürreresistenz KATASTER-DETAIL: Wasserversorgung in der Jugend +, dann Wasserbedarf im Alter +;
    Keywords: Brandenburg ; 1946-48 ; Getreide ; Korrelationsmethode ; Temperatur ; Witterung
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  • 2
    Publication Date: 1949
    Description: Der Autor untersuchte im Freiland die Zeiten zu denen Ausschlüpfen, Begattung und Eiablage des Springwurmwicklers stattfindet. Zudem wurden Temperatur und relative Luftfeuchte gemessen und mit den Beobachtungen zum Schaderreger in Verbindung gesetzt. KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Breisgau, Freiburg ; 1943-1944 ; Luftfeuchte ; Pflanzenschädling ; Temperatur ; Wein
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  • 3
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    In:  Nachr. Bl. Biolog. Ztr.-Anst. Braunschweig, p.19
    Publication Date: 1949
    Description: Verbale Beschreibung des Massenauftretens 1948 sowie früheren Massenauftretens (1891, 1922, 1925, 1938 und 1939) KATASTER-BESCHREIBUNG: Zusammenhang zwischen Witterung (Temperatur und Luftfeuchte) und dem Massenauftreten des Käfers KATASTER-DETAIL: Delta T + (Sommer und Winter) und Delta Relf (Sommer) -, dann Massenauftreten im Folgejahr
    Keywords: Deutschland ; 1947-1948 ; Zuckerrüben ; Pflanzenschädling ; Temperatur ; Trockenheit ; Witterung ; Gemüse
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  • 4
    Publication Date: 1949
    Description: Bericht über die Untersuchungen der mikroklimatischen Temperatur- und Feuchtigkeitsbedingungen in Ackerbohnenbeständen sowie über die Beobachtungen des biogenen Vorganges KATASTER-BESCHREIBUNG: Zusammenhang zwischen der Witterung (Temperatur und Luftfeuchte) und der Stärke des Sporenaustritts KATASTER-DETAIL: Delta T und Delta Relf: 8°C 〈 T 〈 22°c und t (Relf 〉 90%) 〉 8h, dann Sporenaustritt ++; t (Benetzung mit tropfbar flüssigem Wasser) +, dann Sporenaustritt +
    Keywords: Sachsen-Anhalt ; 1948 ; Luftfeuchte ; Pflanzenkrankheit ; Temperatur ; Witterung ; Benetzung ; Gemüse
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  • 5
    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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  • 6
    Publication Date: 2019-07-11
    Description: A large number of papers have been devoted to the problem of integration of equations of two-dimensional steady nonvertical adiabatic motion of a gas. Most of these papers are based on the application of the hodograph method of S. A. Chaplygin in which the plane of the hodograph of the velocity is taken as the region of variation of the independent variables in the equations of motion; the equations become linear in this plane. The exact integration of these equations is, however, obtained in the form of infinite series containing hypergeometric functions. The obtaining of such solutions and their investigation involves extensive computations. As a result, methods have been developed for the approximate integration of the equations of motion first transformed to a linear form. S. A. Chaplygin first pointed out such an approximate method applicable to flows in which the Mach number does not exceed 0.4.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1239 , Prikladnaia Matematika I Mekhanika, Tom XI
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  • 7
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    In:  CASI
    Publication Date: 2019-07-11
    Description: A study is made herein of the irrotational adiabatic motion of a gas in the transition from subsonic to supersonic velocities. A shape of the de Laval nozzle is given, which transforms a homogeneous plane-parallel flow at large subsonic velocity into a supersonic flow without any shockwaves beyond the transition line from the subsonic to the supersonic regions of flow. The method of solution is based on integration near the transition line of the gas equations of motion in the form investigated by S. A. Christianovich.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1236 , Prikladnaia Matematika I Mekhanika, Tom XI
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  • 8
    Publication Date: 2019-07-11
    Description: By means of characteristics theory, formulas for the numerical treatment of stationary compressible supersonic flows for the two-dimensional and rotationally symmetrical cases have been obtained from their differential equations.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1211 , ZWB Forschungsbericht; Rept-1581
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  • 9
    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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  • 10
    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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  • 11
    Publication Date: 2019-08-13
    Description: A heat-transfer investigation was conducted with air flowing through an electrically heated silicon carbide tube with a rounded entrance, an inside diameter of 3/4 inch, and effective heat-transfer length of 12 inches over a range of Reynolds numbers up to 300,000 and a range of average inside-tube-wall temperatures up to 2500 R. The highest corresponding local outside-tube-wall temperature was 3010 R.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA/RM-E9D12
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  • 12
    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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  • 13
    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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  • 14
    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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  • 15
    Publication Date: 2019-07-11
    Description: The calculation of the phenomena within the boundary layer of bodies immersed in a flow underwent a decisive development on the basis of L. Prandtl's trains of thought, stated more than forth years ago, and by numerous later treatises again and again touching upon them. The requirements of the steadily improving aerodynamics of airplanes have greatly increased with the passing of time and recently research became particularly interested in such phenomena in the boundary layer as are caused by small external disturbances. Experimental results suggest that, for instance, slight fluctuations in the free stream velocities as they occur in wind tunnels or slight wavelike deviations of outer wing contours from the prescribed smooth course as they originate due to construction inaccuracies may exert strong effects on the extent of the laminar boundary layer on the body and thus on the drag. The development of turbulence in the last part of the laminar portion of the boundary layer is, therefore, the main problem, the solution of which explains the behavior of the transition point of the boundary layer. A number of reports in literature deal with this problem,for instance, those of Tollmien, Schlichting, Dryden, and Pretsch. The following discussion of the behavior of the laminar boundary layer for periodically oscillating pressure variation also purports to make a contribution to that subject.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1228 , Ludwig Prandtl zum 70. Geburtstage, Schriften der Deutschen Akademie der Luftfahrtforschung, Publications of the Germany academy for Aviation Research; 247-255
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  • 16
    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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  • 17
    Publication Date: 2019-07-11
    Description: This paper includes the following topics: 1) Characteristic differential equations; 2) Treatment of practical examples; 3) First example: Diffuser; and 4) Second Example: Nozzle.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1244 , Chapter 4, Technische Hoschschule Dresden, Archives No. 44; Rept-44/4
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  • 18
    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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  • 19
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    In:  CASI
    Publication Date: 2019-07-13
    Description: The recent experiments by Jakob and Erk, on the resistance of flowing water in smooth pipes, which are in good agreement with earlier measurements by Stenton and Pannell, have caused me to change my opinion that the empirical Blasius law (resistance proportional to the 7/4 power of the mean velocity) was applicable up to arbitrarily high Reynolds numbers. According to the new tests the exponent approaches 2 with increasing Reynolds number, where it remains an open question whether or not a specific finite limiting value of the resistance factor lambda is obtained at R = infinity. With the collapse of Blasius' law the requirements which produced the relation that the velocity in the proximity of the wall varied in proportion to the 7th root of the wall distance must also become void. However, it is found that the fundamental assumption that led to this relationship can be generalized so as to furnish a velocity distribution for any empirical resistance law. These fundamental assumptions can be so expressed that for the law of velocity distribution in proximity of the wall as well as for that of friction at the wall, a form can be found in which the pipe diameter no longer occurs, or in other words, that the processes in proximity of a wall are not dependent upon the distance of the opposite wall.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1231 , Zeitschrift fuer Angewandte Matematik und Mechanik; 5; 2; 136-139
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  • 20
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    In:  CASI
    Publication Date: 2019-07-13
    Description: The flow about a conical body of an ideal compressible fluid is considered. Assume that the velocity of the oncoming flow at infinity W is directed along the z-axis. The system of Cartesian coordinates x, y, z with origin at the vertex of the cone O is shown. From the considerations,of the dimensional theory, it may be found that along any ray issuing from O the components of the velocity u, v, W+w along the coordinate axes will maintain a constant value. It is further assumed that the conical body has such shape and disposition relative to the flow that u, v, and w are small in comparison with W.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1245 , Prikladnaya Matematika I Mekhanika; X; 513-520
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  • 21
    Publication Date: 2019-07-13
    Description: For a certain Mach number of the oncoming flow, the local velocity first reaches the value of the local velocity of sound (M = 1) at some point on the surface of the body located within the flow. This Mach number is designated the critical Mach number M(sub cr). By increasing the flow velocity, a supersonic local region is formed bounded by the body contour and the line of transition from subsonic to supersonic velocity. As is shown by observations with the Toepler apparatus, at a certain flow Mach number M 〉 M(sub cr) a shock wave is formed near the body that closes the local supersonic region from behind. The formation of the shock wave is associated with the appearance of an additional resistance defined as the wave drag. In this paper, certain features are described of the flow in the local supersonic region, which is bounded by the contour of the body and the transition line, and conditions are sought for which the potential flow with the local supersonic region becomes impossible and a shock wave occurs. In the first part of the paper, the general properties of the potential flow in the local supersonic region, bounded by the contour of the profile and the transition line, are established. It is found that at the transition line, if it is not a line of discontinuity, the law of monotonic variation of the angle of inclination of the velocity vector holds (monotonic law). An approximation is given for the change in velocity at the contour of the body. The flow about a contour having a straight part is studied. In the second part of the paper, an approximation is given of the magnitudes of the accelerations at the interior points of the supersonic region. With the aid of these approximations, it is shown that for profiles convex to the flow the breakdown of the potential flow,associated with an increase of the Mach number of the oncoming flow, cannot be due to the formation of an envelope of the characteristics within the supersonic region. On the basis of the monotonic law, the transitional Mach number M is found, beyond which the potential flow with local supersonic region becomes impossible.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1213 , Prikladnaya Matematika i Mekhanika; 10; 4; 481-502
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  • 22
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    In:  CASI
    Publication Date: 2019-07-13
    Description: In the present paper, the motion of a gas in a plane-parallel Laval nozzle in the neighborhood of the transition from subsonic to supersonic velocities is studied. In a recently published paper, F. I. Frankl, applying the holograph method of Chaplygin, undertook a detailed investigation of the character of the flow near the line of transition from subsonic to supersonic velocities. From the results of Tricomi's investigation on the theory of differential equations of the mixed elliptic-hyperbolic type, Frankl introduced as one of the independent variables in place of the modulus of the velocity, a certain specially chosen function of this modulus. He thereby succeeded in explaining the character of the flow at the point of intersection of the transition line and the axis of symmetry (center of the nozzle) and in studying the behavior of the stream function in the neighborhood of this point by separating out the principal term having, together with its derivatives, the maximum value as compared with the corresponding corrections. This principal term is represented in Frankl's paper in the form of a linear combination of two hypergeometric functions. In order to find this linear combination, it is necessary to solve a number of boundary problems, which results in a complex analysis. In the investigation of the flow with which this paper is concerned, a second method is applied. This method is based on the transformation of the equations of motion to a form that may be called canonical for the system of differential equations of the mixed elliptic-hyperbolic type to which the system of equations of the motion of an ideal compressible fluid refers. By studying the behavior of the integrals of this system in the neighborhood of the parabolic line, the principal term of the solution is easily separated out in the form of a polynomial of the third degree. As a result, the computation of the transitional part of the nozzle is considerably simplified.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1212 , Prikladnaya Matematika I Mekhanika; 10; 4; 503-512
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  • 23
    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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  • 24
    Publication Date: 2019-07-11
    Description: The authors regret that due to the lack of time the investigations could not be carried out to a more finished form. Especially in the first part it was intended to include a few further applications and to use them in the general considerations of this part. In spite of the fact that the intentions of the authors could not be realized, the authors felt that it would serve the aims of the competition to present part I in its present fragmentary form. The topics include: 1) A Few General Remarks Covering the Prandtl-Busemann Method; and 2) Effect of Compressibility in Axially Symmetrical Flow around an Ellipsoid.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1233 , Lilienthal-Gesellschaft fuer Luftfahrtforschung Bericht S 13/1, Part 1; 40-68; Rept-13/1
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  • 25
    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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  • 26
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    In:  CASI
    Publication Date: 2019-07-11
    Description: In the present paper which deals with the heat transfer between the gas and the wall for large temperature drops and large velocities use is made of the method of Dorodnitsyn of the introduction of a new independent variable, with this difference, however, that the relation between the temperature field (that is, density) and the velocity field in the general case considered is not assumed given but is determined from the solution of the problem. The effect of the compressibility arising from the heat transfer is thus taken into account (at the same time as the effect of the compressibility at the large velocities). A method is given for determining the coefficients of heat transfer and the friction coefficients required in many technical problems for a curved wall in a gas flow at large Mach numbers and temperature drops. The method proposed is applicable both for Prandtl number P = 1 and for P not equal to 1.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1229 , Prikladnaya Matematika I Mekhanika, Tom X; 449-474
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  • 27
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    In:  CASI
    Publication Date: 2019-07-11
    Description: There has been under development for the high-speed wind tunnel of the LFA an optical measuring arrangement for the qualitative and quantitative investigation of flow. By the use of interference measurements, the determination of density at the surface of the bodies being tested in the air stream and in the vicinity of these bodies can be undertaken. The results obtained so far in the simple preliminary investigations show that it is possible, even at a low Reynolds number, to obtain the density field in the neighborhood of a test body by optical means. Simple analytical expressions give the relation between density, pressure, velocity, and temperature. In addition to this, the interference measurement furnishes valuable data on the state of the boundary layer, that is, the sort of boundary layer (whether laminar or turbulent), as well as the temperature and velocity distribution.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1253 , Forschungsbericht; Rept-1167
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  • 28
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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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  • 29
    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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  • 30
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    In:  CASI
    Publication Date: 2019-07-11
    Description: The flow laws of the actual flows at high Reynolds numbers differ considerably from those of the laminar flows treated in the preceding part. These actual flows show a special characteristic, denoted as turbulence. The character of a turbulent flow is most easily understood the case of the pipe flow. Consider the flow through a straight pipe of circular cross section and with a smooth wall. For laminar flow each fluid particle moves with uniform velocity along a rectilinear path. Because of viscosity, the velocity of the particles near the wall is smaller than that of the particles at the center. i% order to maintain the motion, a pressure decrease is required which, for laminar flow, is proportional to the first power of the mean flow velocity. Actually, however, one ob~erves that, for larger Reynolds numbers, the pressure drop increases almost with the square of the velocity and is very much larger then that given by the Hagen Poiseuille law. One may conclude that the actual flow is very different from that of the Poiseuille flow.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1218
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  • 31
    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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  • 32
    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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  • 33
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    In:  CASI
    Publication Date: 2019-07-11
    Description: Contents include the following: Characteristic differential equations - initial and boundary conditions. Integration of the second characteristic differential equations. Direct application of Meyer's characteristic hodograph table for construction of two-dimensional potential flows. Prandtl-Busemann method. Development of the pressure variation for small deflection angles. Numerical table: relation between deflection, pressure, velocity, mach number and mach angle for isentropic changes of state according to Prandtl-Meyer for air (k = 1.405). References.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1243 , Chapter 3,Technische Hochschule Dresden, Archives No. 44/3; Rept-44/3
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  • 34
    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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  • 35
    Publication Date: 2019-07-11
    Description: A heat-transfer investigation was conducted with air flowing through an electrically heated silicon carbide tube with a rounded entrance, an inside diameter of 3/4 inch, and an effective heat-transfer length of 12 inches over a range of Reynolds numbers up to 300,000 and a range of average inside-tube-wall temperature up to 2500 R. The highest corresponding local outside-tube-wall temperature was 3010 R. Correlation of the heat-transfer data using the conventional Nueselt relation wherein physical properties of the fluid were evaluated at average bulk temperature resulted in a separation of data with tube-wall-temperature level. A satisfactory correlation of the heat-transfer data was obtained, however, by the use of modified correlation parameters wherein the mass velocity G (or product of average air density and velocity evaluated at bulk temperature P(sub b)V(sub b)) in the Reynolds number was replaced by the product of average air velocity evaluated at the bulk temperature and density evaluated at either the average inside-tube-wall temperature or the average film temperature; in addition, all the physical properties of air were correspondingly evaluated at either the average inside-tube-wall temperature or the average film temperature.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-RM-E9D12-Pt-3 , Rept-1115-Pt-3
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  • 36
    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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  • 37
    Publication Date: 2019-07-10
    Description: In the lecture series starting today author want to give a survey of a field of aerodynamics which has for a number of years been attracting an ever growing interest. The subject is the theory of flows with friction, and, within that field, particularly the theory of friction layers, or boundary layers. A great many considerations of aerodynamics are based on the ideal fluid, that is the frictionless incompressibility and fluid. By neglect of compressibility and friction the extensive mathematical theory of the ideal fluid, (potential theory) has been made possible. Actual liquids and gases satisfy the condition of incomressibility rather well if the velocities are not extremely high or, more accurately, if they are small in comparison with sonic velocity. For air, for instance, the change in volume due to compressibility amounts to about 1 percent for a velocity of 60 meters per second. The hypothesis of absence of friction is not satisfied by any actual fluid; however, it is true that most technically important fluids, for instance air and water, have a very small friction coefficient and therefore behave in many cases almost like the ideal frictionless fluid. Many flow phenomena, in particular most cases of lift, can be treated satisfactorily, - that is, the calculations are in good agreement with the test results, -under the assumption of frictionless fluid. However, the calculations with frictionless flow show a very serious deficiency; namely, the fact, known as d'Alembert's paradox, that in frictionless flow each body has zero drag whereas in actual flow each body experiences a drag of greater or smaller magnitude. For a long time the theory has been unable to bridge this gap between the theory of frictionless flow and the experimental findings about actual flow. The cause of this fundamental discrepancy is the viscosity which is neglected in the theory of ideal fluid; however, in spite of its extraordinary smallness it is decisive for the course of the flow phenomena.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1217
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  • 38
    Publication Date: 2019-07-12
    Description: Wind-tunnel tests of a full-scale model of the Republic XF-91 airplane having swept-back wings and a vee tail were conducted to determine both the stability and control characteristics of the model longitudinally, laterally, and directionally. Configurations of the model were investigated involving such variables as external fuel tanks, a landing gear, trailing-edge flaps, leading-edge slats, and a range of wing incidences and tail incidences.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-RM-SA9C04
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  • 39
    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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  • 40
    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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  • 41
    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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  • 42
    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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  • 43
    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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  • 44
    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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  • 45
    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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  • 46
    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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  • 47
    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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  • 48
    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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  • 49
    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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  • 50
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    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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  • 51
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    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.
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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 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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  • 53
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    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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  • 54
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 19-24 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    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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  • 55
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 15-18 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    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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    Chemie Ingenieur Technik - CIT 21 (1949), S. 24-30 
    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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    Chemie Ingenieur Technik - CIT 21 (1949), S. 31-31 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 31-32 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 33-37 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 37-38 
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    Keywords: Chemistry ; Industrial Chemistry
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 38-38 
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    Keywords: Chemistry ; Industrial Chemistry
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 32-32 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 39-39 
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    Keywords: Chemistry ; Industrial Chemistry
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 40-40 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 39-40 
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    Keywords: Chemistry ; Industrial Chemistry
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 40-40 
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 47-47 
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 41-41 
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    Chemie Ingenieur Technik - CIT 21 (1949), S. 41-42 
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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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    Source: Wiley InterScience Backfile Collection 1832-2000
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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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