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  • 1990-1994  (3)
  • 1940-1944  (18,777)
  • 1944  (18,777)
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Year
  • 1
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    Unknown
    In:  Leidse Geologische Mededelingen vol. 14 no. 1, pp. 10-39
    Publication Date: 2024-01-12
    Description: De koralenfauna van het Tertiair van Nederland was tot nu toe zeer onvolledig bekend. Krejci (1925) noemde het voorkomen van Flabellum cristatum, Fl. Pompeckji en Fl. Waelii, var. Dingdenensis van de Giffel bij Winterswijk en van Fl. Waelii van Maasbree. Vervolgens noemde Burck (1937) uit het Bartonien van Buurse en Boekelo een drietal koralen. Dit is alles wat ik aan gegevens over Nederlandsche koralen uit het Tertiair in de nieuwere literatuur heb kunnen vinden.\nNaast de, vaak zeer rijke, molluskenfauna van het Tertiair spelen de koralen dan ook een ondergeschikte rol en de meeste vormen zijn als gidsfossiel bovendien slecht te gebruiken, daar ze zich haast onveranderd in de verschillende formaties voortzetten. Vooral door het optreden van vele Flabellumsoorten heeft de rijke midden-miocene koralenfauna wel een zeer eigen beeld.
    Repository Name: National Museum of Natural History, Netherlands
    Type: info:eu-repo/semantics/article
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  • 2
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    In:  Leidse Geologische Mededelingen vol. 14 no. 1, pp. 1-9
    Publication Date: 2024-01-12
    Description: Das am 21. November 1942 im beinahe vollendeten 92. Lebensjahr erfolgte Dahinscheiden des um die geologische Erforschung der niederl\xc3\xa4ndischen Kolonien in Ost- und Westindien so hoch verdienten Gelehrten veranlasst mich in dieser Zeitschrift, die ja die Fortsetzung der von Martin gegr\xc3\xbcndeten \xe2\x80\x9eSammlungen des Geologischen Reichsmuseum\xe2\x80\x9d ist, noch einmal auf die wissenschaftliche Bedeutung seines Lebenswerkes zur\xc3\xbcckzukommen. Die erfolgreiche T\xc3\xa4tigkeit Martin\xe2\x80\x99s als Dozent und Direktor des Reichsmuseum f\xc3\xbcr Geologie und Mineralogie ist in der, anl\xc3\xa4sslich seines 80. Geburtstages herausgegebenen Festschrift 1) schon eingehend gew\xc3\xbcrdigt worden, auf seine wissenschaftliche T\xc3\xa4tigkeit wurde bei dieser Gelegenheit nur kurz hingewiesen, sie war damals ja noch nicht abgeschlossen.\nWaren es auch namentlich die gr\xc3\xbcndlichen Untersuchungen und eingehenden Beschreibungen der Mollusken aus dem Terti\xc3\xa4r von Java, die Martin bei den Pal\xc3\xa4ontologen der ganzen Welt bekannt gemacht haben, so war er doch keineswegs nur Molluskenspezialist. Wir sehen, dass seine Aufs\xc3\xa4tze in den Sammlungen die Untersuchungen von Fossilien aus fast allen Tiergruppen und den verschiedensten Formationen des indischen Archipel enthalten und h\xc3\xa4ufig waren die darauf gegr\xc3\xbcndeten Altersbestimmungen f\xc3\xbcr die weitere geologische Erforschung der betreffenden Gebiete grundlegend. Martin war aber ebensowenig wie ausgesprochener Molluskenspezialist auch nur Pal\xc3\xa4ontologe. 1884 unternahm er mit einigen holl\xc3\xa4ndischen Forschern eine Reise nach Westindien. Die ersten geologischen Karten von Cura\xc3\xa7ao, Bonaire und Aruba, sowie eine geologische Aufnahme des unteren Suriname in niederl\xc3\xa4ndisch Guyana waren die wesentlichen Ergebnisse dieser Reise. 1891/92 befand sich Martin auf einer geologischen Forschungsreise in Ostindien, wo er namentlich einige Inseln der westlichen Molukken erforschte, die geologisch damals noch ganz unbekannt waren. Eine besondere Leistung, f\xc3\xbcr die damalige Zeit war seine Durchquerung der Insel Buru, deren Ergebnisse lange Zeit unser einziges Wissen vom geologischen Bau dieser Insel darstellten. So kann Martin mit Recht zu den Pionieren in der geologischen Erforschung des Indischen Archipels gerechnet werden.
    Repository Name: National Museum of Natural History, Netherlands
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  • 3
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    In:  Leidse Geologische Mededelingen vol. 14 no. 1, pp. 40-58
    Publication Date: 2024-01-12
    Description: An upper molar of Anancus arvernensis (Croiz. & Job.), fished out of the Eastern Scheldt, near Ierseke, and belonging to the so-called black fossils, shows more affinity with the specimens from the English Crags than with those from Th\xc3\xbcringen. Another upper molar of the species has been dredged out of the Lower-Rhine.\nA lower molar of Archidiskodon planifrons (Falc. & Caut.) from the same locality as the first-named tooth, and displaying the same kind of fossilization has most probably been washed out of the same deposit. Also in other parts of Europe the two animals lived together in the Upper-Pliocene, prae-G\xc3\xbcnzian period. Marine Amstelian deposits being absent in the greater part of Zealand, it is highly probable that a fauna of landmammals to which also both Proboscidea, belong, thus resembling other Lower-Villafranchian faunas like those of Italy, Auvergne and the English Red Crag, also lived in Zealand when this region emerged above the sea.
    Repository Name: National Museum of Natural History, Netherlands
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  • 4
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    PANGAEA
    In:  Supplement to: Revelle, Roger (1944): Marine bottom samples collected in the Pacific Ocean by the Carnegie on its seventh cruise. In: Scientific Results of Cruise VII of the CARNEGIE during 1928-1929 under Command of Captain J. P. Ault, Oceanography. Carnegie Institution of Washington, Washington D.C., USA, 180 pp, https://archive.org/details/imarinebottomsam00carn
    Publication Date: 2023-08-28
    Description: The Carnegie, on its seventh cruise and last cruise, collected seventy-five samples of deep-sea deposits in the southeastern and the north Pacific. This report contains an account of the general character of the deep-sea samples collected and of the distribution of the various deposit types, together with the results of chemical, mechanical, X-ray, and other types of analyses. As indicated in the text, many of the analyses were carried out in whole or in part by other investigators.
    Keywords: CARN_Revelle_10; CARN_Revelle_11; CARN_Revelle_15; CARN_Revelle_17; CARN_Revelle_22; CARN_Revelle_24; CARN_Revelle_46; CARN_Revelle_47; CARN_Revelle_57; CARN_Revelle_67; CARN_Revelle_70; CARN_Revelle_71; CARN_Revelle_72; CARN_Revelle_75; CARN_Revelle_77; CARN_Revelle_78; CARN_Revelle_79; CARN_Revelle_81; CARN_Revelle_82; CARN7-115; CARN7-134; CARN7-137; CARN7-138; CARN7-142; CARN7-147; CARN7-149; CARN7-150; CARN7-151; CARN7-156; CARN7-157; CARN7-37; CARN7-40; CARN7-46; CARN7-49; CARN7-59; CARN7-61; CARN7-86; CARN7-87; CARN-Cruise7; Carnegie; Comment; Deposit type; DEPTH, sediment/rock; Description; Dredge; DRG; Event label; NOAA and MMS Marine Minerals Geochemical Database; NOAA-MMS; Pacific Ocean; Position; Quantity of deposit; Sample ID; Sediment type; Size; Substrate type; Visual description
    Type: Dataset
    Format: text/tab-separated-values, 151 data points
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  • 5
    Journal available for loan
    Journal available for loan
    Tübingen : Mohr Siebeck ; 1.1884 - 48.1931; N.F. 1.1932/33 - 10.1943/44(1945),3; 11.1948/49(1949) -
    Call number: ZS 22.95039
    Type of Medium: Journal available for loan
    Pages: Online-Ressource
    ISSN: 1614-0974 , 0015-2218 , 0015-2218
    Language: German , English
    Note: N.F. entfällt ab 57.2000. - Volltext auch als Teil einer Datenbank verfügbar , Ersch. ab 2000 in engl. Sprache mit dt. Hauptsacht.
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  • 6
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    Poeschel & Trepte
    In:  Veröffentlichung des Geodätischen Institutes
    Publication Date: 2020-02-12
    Language: German
    Type: info:eu-repo/semantics/report
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  • 7
    Publication Date: 2019-08-17
    Description: Theoretical investigations have shown that, because air is compressible, the pressure-drop requirements for cooling an air-cooled engine will be much greater at high altitudes and high speeds than at sea level and low speeds. Tests were conducted by the NACA to obtain some experimental confirmation of the effect of air compressibility on cooling and pressure loss of a baffled cylinder barrel and to evaluate various methods of analysis. The results reported in the present paper are regarded as preliminary to tests on single-cylinder and multi-cylinder engines. Tests were conducted over a wide range of air flows and density altitudes.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TR-783
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  • 8
    Publication Date: 2019-08-16
    Description: An analysis is made of the stability of an airplane with ailerons free, with particular attention to the motions when the ailerons have a tendency to float against the wind. The present analysis supersedes the aileron investigation contained in NACA Report No. 709. The equations of motion are first written to include yawing and sideslipping, and it is demonstrated that the principal effects of freeing the ailerons can be determined without regard to these motions. If the ailerons tend to float against the wind and have a high degree of aerodynamic balance, rolling oscillations, in addition to the normal lateral oscillations, are likely to occur. On the basis of the equations including only the rolling motion and the aileron deflection, formulas are derived for the stability and damping of the rolling oscillations in terms of the hinge moment derivatives and other characteristics of the ailerons and airplane. Charts are also presented showing the oscillatory regions and stability boundaries for a fictitious airplane of conventional proportions. The effects of friction in the control system are investigated and discussed. If the ailerons tend to trail with the wind, the condition for stable variation of stick force with aileron deflection is found to determine the amount of aerodynamic balance that may be used. If the ailerons tend to float against the wind, the period and damping of the rolling oscillations are found to be satisfactory (in a mass-balanced system) so long as the restoring moment is not completely balanced out. Unbalanced mass behind the hinge, however, has an unfavorable effect on the damping of the oscillations and so shifts the boundary that close aerodynamic balance may not be attainable.
    Keywords: Aircraft Design, Testing and Performance
    Type: AD-A301275 , NACA-TR-787 , NASA-TM-111361 , NAS 1.15:111361
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  • 9
    Publication Date: 2019-08-15
    Description: The differential equation of Chaplygin's jet problem is utilized to give a systematic development of particular solutions of the hodograph flow equations, which extends the treatment of Chaplygin into the supersonic range and completes the set of particular solutions. The particular solutions serve to place on a reasonable basis the use of velocity correction formulas for the comparison of incompressible and compressible flows. It is shown that the geometric-mean type of velocity correction formula introduced in part I has significance as an over-all type of approximation in the subsonic range. A brief review of general conditions limiting the potential flow of an adiabatic compressible fluid is given and application is made to the particular solutions, yielding conditions for the existence of singular loci in the supersonic range. The combining of particular solutions in accordance with prescribed boundary flow conditions is not treated in the present paper.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA/TR-790
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  • 10
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    In:  CASI
    Publication Date: 2019-08-15
    Description: A brief summary of the contents of this paper is presented here. In part I the differential equations of the problem of a gas flow in two dimensions is derived and the particular integrals by which the problem on jets is solved are given. Use is made of the same independent variables as Molenbroek used, but it is found to be more suitable to consider other functions. The stream function and velocity potential corresponding to the problem are given in the form of series. The investigation on the convergence of these series in connection with certain properties of the functions entering them forms the subject of part II. In part III the problem of the outflow of a gas from an infinite vessel with plane walls is solved. In part IV the impact of a gas jet on a plate is considered and the limiting case where the jet expands to infinity changing into a gas flow is taken up in more detail. This also solved the equivalent problem of the resistance of a gaseous medium to the motion of a plate. Finally, in part V, an approximate method is presented that permits a simpler solution of the problem of jet flows in the case where the velocities of the gas (velocities of the particles in the gas) are not very large.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1063 , Scientific Memoirs; 1-121
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  • 11
    Publication Date: 2019-08-15
    Description: Pressure distribution and spray measurements were carried out on rectangular flat and V-bottom planing surfaces. Lift, resistance, and center of pressure data are analyzed and it is shown how these values may be computed for the pure planing procees of a flat or V-bottom suface of arbitrary beam, load and speed, the method being illustrated with the aid of an example.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1061 , Jahrbuch 1937 der Deutschen Luftfahrtforschung; 320-339
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  • 12
    Publication Date: 2019-08-13
    Description: This report outlines the flight conditions that are usually critical in determining the design of components of an airplane which affect its stability and control characteristics. The wind-tunnel tests necessary to determine the pertinent data for these conditions are indicated, and the methods of computation used to translate these data into characteristics which define the flying qualities of the airplane are illustrated.
    Keywords: Aircraft Stability and Control
    Type: NACA/TR-781
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  • 13
    Publication Date: 2019-08-13
    Description: Problems relating to the stability and control of tailless airplanes are discussed in consideration of contemporary experience and practice.
    Keywords: Aircraft Stability and Control
    Type: NACA/TR-796
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  • 14
    Publication Date: 2019-08-13
    Description: Field measurements were made on a fighter airplane to determine the approximate magnitude of the horizontal tail loads in accelerated flight. In these flight measurements, pressures at a few points were used as an index of the tail loads by correlating these pressures with complete pressure-distribution data obtained in the NACA full-scale tunnel. In addition, strain gages and motion pictures of tail deflections were used to explore the general nature and order of magnitude of fluctuating tail loads in accelerated stalls.
    Keywords: Aircraft Stability and Control
    Type: NACA/TR-792
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  • 15
    Publication Date: 2019-08-13
    Description: An experimental investigation concerned primarily with the extension of test data on the drag of revolving disks, cylinders, and streamline rods to high Mach numbers and Reynolds numbers is presented.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TR-793
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  • 16
    Publication Date: 2019-08-13
    Description: The relation between the elevator hinge-moment parameters and the control-forces for changes in forward speed and in maneuvers is shown for several values of static stability and elevator mass balance.
    Keywords: Aircraft Stability and Control
    Type: NACA/TR-791
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  • 17
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    PANGAEA
    In:  EPIC3Records of observations, Scripps Institution of Oceanography, University of California Press, Berkley and Los Angeles, Bremerhaven, PANGAEA, 1(3), pp. 161-248
    Publication Date: 2019-07-17
    Repository Name: EPIC Alfred Wegener Institut
    Type: PANGAEA Documentation , notRev
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  • 18
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    In:  CASI
    Publication Date: 2019-07-13
    Description: One of the problems of modern cavitation research is the experimental determination of the wing loads on airfoils during cavitation. Such experiments were made on various airfoils with the support of the naval ministry at the Kaiser Wilhelm Institute for Flow Research at Goettingen.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1060 , Hydromechanical Problems of Ship Propulsion; May 18, 1932 - May 19, 1932; Hamburg; Germany
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  • 19
    Publication Date: 2019-07-13
    Description: The changes produced on metallic surfaces as a result of grinding and polishing are not as yet fully understood. Undoubtedly there is some more or less marked change in the crystal structure, at least, in the top layer. Hereby a diffusion of separated crystal particles may be involved, or, on plastic material, the formation of a layer in greatly deformed state, with possible recrystallization in certain conditions. Czochralski verified the existence of such a layer on tin micro-sections by successive observations of the texture after repeated etching; while Thomassen established, roentgenographically by means of the Debye-Scherrer method, the existence of diffused crystal fractions on the surface of ground and polished tin bars, which he had already observed after turning (on the lathe). (Thickness of this layer - 0.07 mm). Whether this layer borders direct on the undamaged base material or whether deformed intermediate layers form the transition, nothing is known. One observation ty Sachs and Shoji simply states that after the turning of an alpha-brass crystal the disturbance starting from the surface, penetrates fairly deep (approx. 1 mm) into the crystal (proof by recrystallization at 750 C).
    Keywords: Mechanical Engineering
    Type: NACA-TM-1072 , Naturwissenschaften; 20; 22/24; 416-419
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  • 20
    Publication Date: 2019-07-13
    Description: The number of partial contact surfaces of a brush-ring contact is measured by means of a statistical method. The particular brush is fitted with wicks - that is, insulated and cemented cylinders of brush material, terminating in the brush surface. The number of partial contact surfaces can be computed from the length of the rest periods in which such wicks remain without current. Resistance measurements enable the determination of the size of the contact surfaces. The pressure in the actual contact surface of a recently bedded brush is found to be not much lower than the Brinell hardness of the brush.
    Keywords: Electronics and Electrical Engineering
    Type: NACA-TM-1071 , Wissenschaftliche Veroffentlichungen aus den Siemens-Werken; 17; 4; 43-47
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  • 21
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    Unknown
    In:  CASI
    Publication Date: 2019-07-13
    Description: The,theory of heat.transfer from a solid body to a liquid stream could he presented previously** only with limiting assumptions about the movement of the fluid (potential flow, laminar frictional flow). (See references 1, 2, and 3). For turbulent flow, the most important practical case, the previous theoretical considerations did not go beyond dimensionless formulas and certain conclusions as to the analogy between the friction factor and the unit thermal conductance, (See references 4, 5, 6, and 7,) In order to obtain numerical results, an experimental treatment of the problem was resorted to, which gave rise to numerous investigations because of the importance of this problem in many branches of technology. However, the results of these investigations frequently deviate from one another. The experimental results are especially dependent upon the overall dimensions and the specific proportions of the equipment. In the present work, the attempt will be made to develop systematically the theory of the heat transfer and of the dependence of the unit thermal conductance upon shape and dimensions, using as a basis the velocity distribution for turbulent flow set up by Prandtl and Von Karman.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1068 , Zeitschrift fuer Angewandte Mathematik und Mechanik; 1; 4; 268-290
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  • 22
    facet.materialart.
    Unknown
    In:  CASI
    Publication Date: 2019-07-13
    Description: In many studies, especially of nonstationary flight motion, it is necessary to determine the angular velocities at which the airplane rotates about its various axes. The three-component recorder is designed to serve this purpose. If the angular velocity for one flight attitude is known, other important quantities can be derived from its time rate of change, such as the angular acceleration by differentiations, or - by integration - the angles of position of the airplane - that is, the angles formed by the airplane axes with the axis direction presented at the instant of the beginning of the motion that is to be investigated.
    Keywords: Aerodynamics
    Type: NACA-TM-1065 , Luftwissen; 5; 8; 297-298
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  • 23
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    In:  CASI
    Publication Date: 2019-07-13
    Description: The following investigations are connected with experiments on fans carried out by the author in the Gouttingen Aerodynamic Laboratory within the framework of the preliminary experiments for the new Gouttingen wind-tunnel project. A fan rotor was developed which had very high efficiency at the design point corresponding to moderate pressure and which, in addition, could operate at a proportionally high pressure, rise. To establish the determining operating factors the author carried out extensive theoretical investigation in Hannover. In this it was necessary, to depart from the usual assumption of vanishing radial velocities. The calculations were substantially lightened by the introduction of diagrams. The, first part of the.report describes the theoretical investigations; the second, the experiments carried out at Gouttingen.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1062 , Luftfahyrtforschung; 14; 7; 325-346
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  • 24
    Publication Date: 2019-07-13
    Description: The wall interference is obtained for a wind tunnel of elliptic section for the two cases of closed and open working sections. The approximate and exact methods used gave results in practically good agreement. Corresponding to the result given by Glauert for the case of the closed rectangular section, the interference is found to be a minimum for a ratio of minor to major axis of 1:square root of 6 This, however, is true only for the case where the span of the airfoil is small in comparison with the width of the tunnel. For a longer airfoil the favorable ellipse is flatter. In the case of the open working section the circular shape gives the minimum interference.
    Keywords: Aerodynamics
    Type: NACA-TM-1075 , Journal of the Society of Mechanical Engineers; 36; 190; 123-127
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  • 25
    Publication Date: 2019-07-13
    Description: Hardy's statement that the frictional force is largely adhesion, and to a lesser extent, deformation energy is proved by a simple experiment. The actual contact surface of sliding contacts and hence the friction per unit of contact surface was determined in several cases. It was found for contacts in normal atmosphere to be about one-third t-one-half as high as the macroscopic tearing strength of the softest contact link, while contacts annealed in vacuum and then tested, disclosed frictional forces which are greater than the macroscopic strength.
    Keywords: Mechanical Engineering
    Type: NACA-TM-1074 , Wissenschaftliche Veroeffentlichungen aus den Siemens-Werken; 17; 4; 38-42
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  • 26
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    In:  CASI
    Publication Date: 2019-07-13
    Description: In internal combustion engines, steam engines, air compressors, and so forth, the piston ring plays an important role. Especially, the recent development of Diesel engines which require a high compression pressure for their working, makes, nowadays, the packing action of the piston ring far more important than ever. Though a number of papers have been published in regard to researches on the problem of the piston ring, none has yet dealt with an exact measurement of pressure exerted on the cylinder wall at any given point of the ring. The only paper that can be traced on this subject so far is Mr. Nakagawa's report on the determination of the relative distribution of pressure on the cylinder wall, but the measuring method adopted therein appears to need further consideration. No exact idea has yet been obtained as to how the obturation of gas between the piston and cylinder, the frictional resistance of the piston, and the wear of the cylinder wall are affected by the intensity and the distribution of the radial pressure of the piston ring. Consequently, the author has endeavored, by employing an apparatus of his own invention, to get an exact determination of the pressure distribution of the piston ring. By means of a newly devised ring tester, to which piezoelectricity of quartz was applied, the distribution of the radial pressure of many sample rings on the market was accurately determined. Since many famous piston rings show very irregular pressure distribution, the author investigated and achieved a manufacturing process of the piston ring which will exert uniform pressure on the cylinder wall. Temperature effects on the configuration and on the mean spring power have also been studied. Further, the tests were performed to ascertain how the gas tightness of the piston ring may be affected by the number or spring power. The researches as to the frictional resistance between the piston ring and the cylinder wall were carried out, too. The procedure of study, and experiments conducted by the author, on this subject will be fully described in the following paragraphs.
    Keywords: Mechanical Engineering
    Type: NACA-TM-1057 , 32st Rep. of Okochi Res. Lab.: Scientific Papers of the Inst. of Physical and Chemical Research, Tokyo University; 10; 182; 107-185
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  • 27
    Publication Date: 2019-07-12
    Description: The effect of several armament installations on the drag of a 1/8 scale model of the B-32 airplane was determined. Turrets in the following positions were tested: nose, tail, upper forward, upper aft, and lower. The nose and tail turrets were each equipped with two.50-caliber guns. Upper turrets were of three types: two.50-caliber guns, four.50-caliber guns, and 20-millimeter cannon. Lower turrets were of two types: two.50-caliber guns and four.50-caliber guns. The effect of streamlining the upper two- and four-gun turrets and of extending the lower two-gun turret was determined. The tests were conducted in the Langley 19-foot. pressure tunnel at a Reynolds number of approximately 2,960,000 and a Mach number of 0.13. Large increases in drag coefficient were caused by the complete armament installations. At a lift coefficient of 0. 4 the installations with nonstreamlined upper turrets and the lower turret retracted increased the drag coefficient by 0.0022 and 0.0027 for the two-gun and four-gun turret installations, respectively. Streamlining the upper turrets reduced the drag of these installations by approximately 40 percent with the upper turrets streamlined, the drag increase was about the same for either the two- or four-gun turret installation. The streamlined two-cannon upper turrets increased the drag about the same amount as the two-gun upper turrets that were not streamlined. Extension of the lower turret. increased the drag slightly more than the whole streamlined gun-turret installation.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-MR-L4L30a
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  • 28
    Publication Date: 2019-07-12
    Description: This report gives the results of tests on a rectangular wing model with a 20% full spun split flap, conducted on the whirling arm at the Daniel Guggenheim Airship Institute in Akron, Ohio. The effect of a ground board on the lift and pitching moment was measured. The ground board consisted of an inclined ramp rising up in the test channel to a level floor extending for some distance parallel to the model path. The path of the wing model with respect to the ground board accordingly represented with comparative exactness an airplane coming in for a landing. The ground clearances over the level portion of the board varied from 0 6 to 1,6 chord lengths. Results are given in the standard dimensionless coefficients plotted versus angle of attack for a particular ground clearance. The effect of the ground board is to increase the lift coefficient for a given angle of attack all the way up the stall. The magnitude of the increase varies both with the ground clearance and the angle of attack. The effect on the pitching moment coefficient is not so readily apparent due to experimental difficulties but, in general, the diving moment increases over the ground board. This effect is apparent principally at the high angles of attack. An exception to this effect occurs with flaps deflected at the lowest ground clearance (0.6 chords). Here the diving moment decreases over the ground board.
    Keywords: Aerodynamics
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  • 29
    Publication Date: 2019-07-12
    Description: The design and construction of various forms of strain-gage spring units and hinge-moment assemblies are discussed with particular reference to wind-tunnel test, although the indicators may be used equally well in flight tests. Strain-gage specifications are given, and the techniques of their application and use are described briefly. Testing, calibration and operation of hinge-moment indicators are discussed and precautions necessary for successful operation are stressed. Difficulties that may be encountered are summarized along with the possible causes.
    Keywords: Instrumentation and Photography
    Type: NACA-CB-L4D15
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  • 30
    Publication Date: 2019-07-12
    Description: A discussion of the interaction between normal shocks and boundary layers on the basis of experimental evidence obtained in studies of supersonic flows in passages is given. The investigation was made as a result of the inability of the existing normal-shock theory to explain phenomena involving normal shocks that occurred in the presence of boundary layers. Assumptions with regard to the character of the effects of interaction between boundary layer and normal shock are proposed; these assumptions seem to give good agreement with certain experimental results.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-CB-4A27
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  • 31
    Publication Date: 2019-07-12
    Description: Results are presented of tests to determine the column and plate compressive strength of extruded XB75S-T aluminum alloy, and comparative values are shown for 24S-T aluminum-alloy sheet. Stress-strain curves are also given,
    Keywords: Metals and Metallic Materials
    Type: NACA RB No. L4E26
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  • 32
    Publication Date: 2019-07-12
    Description: In this report a method is presented for the calculation of the profile drag of airfoil sections. The method requlres only a knowledge of the theoretical velocity distribution and can be applied readily once this dlstribution is ascertained. Comparison of calculated and experimental drag characteristics for several airfoils shows a satisfactory agreement. Sample calculatlons are included.
    Keywords: Aerodynamics
    Type: NACA ACR No. 4B05
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  • 33
    Publication Date: 2019-07-11
    Description: This paper presents the results of tests conducted to determine the effect of the constructional elements of a Laval nozzle on the velocity and pressure distribution and the magnitude of the reaction force of the jet. The effect was studied of the shapes of the entrance section of the nozzle and three types of divergent sections: namely, straight cone, conoidal with cylindrical and piece and diffuser obtained computationally by a graphical method due to Professor F. I. Frankle. The effect of the divergence angle of the nozzle on the jet reaction was also investigated. The results of the investigation showed that the shape of the generator of the inner surface of the entrance part of the nozzle essentially has no effect on the character of the flow and on the reaction. The nozzle that was obtained by graphical computation assured the possibility of obtaining a flow for which the velocity of all the gas particles is parallel to the axis of symmetry of the nozzle, the reaction being on the average 2 to 3 percent greater than for the usual conical nozzle under the same conditions, For the conical nozzle the maximum reaction was obtained for a cone angle of 25deg to 27deg. At the end of this paper a sample computation is given by the graphical method. The tests were started at the beginning of 1936 and this paper was written at the same time.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1066 , Report of the Central Aero-Hydrodynamical Inst., Moscow; Rept-478
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  • 34
    Publication Date: 2019-07-11
    Description: The present report deals with the determination of the impact stresses in the bulkhead floors of a seaplane bottom. The dynamic problem is solved on the assumption of a certain elastic system, the floor being assumed as a weightless elastic beam with concentrated masses at the ends (due to the mass of the float) and with a spring which replaces the elastic action of the keel in the center. The distributed load on the floor is that due to the hydrodynamic force acting over a certain portion of the bottom. The pressure distribution over the width of the float is assumed to follow the Wagner law. The formulas given for the maximum bending moment are derived on the assumption that the keel is relatively elastic, in which case it can be shown that at each instant of time the maximum bending moment is at the point of juncture of the floor with the keel. The bending moment at this point is a function of the half width of the wetted surface c and reaches its maximum value when c is approximately equal to b/2 where b is the half width of the float. In general, however, for computing the bending moment the values of the bending moment at the keel for certain values of c are determined and a curve is drawn. The illustrative sample computation gave for the stresses a result approximately equal to that obtained by the conventional factory computation.
    Keywords: Aircraft Stability and Control
    Type: NACA-TM-1055 , Report of the Central Aero-Hydrodynamical Inst., Moscow; Rept-449
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  • 35
    facet.materialart.
    Unknown
    In:  CASI
    Publication Date: 2019-07-11
    Description: The paper describes nethods of computing the stresses in disks of a given profile as well as methods of choosing the disk profiles for a given stress distribution for turhines, turbo blowers, and so forth. A new method of in tegrating the differential equations of Stodola leads to a simplification of the computation for disks of hyperbolic profile.
    Keywords: Numerical Analysis
    Type: NACA-TM-1064
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  • 36
    Publication Date: 2019-07-11
    Description: To determine the effect of piston-head temperature on knock-limited power. Tests were made in a supercharged CFR engine over a range of fuel-air ratios from 0.055 to 0.120, using S-3 reference fuel, AN-F-28, Amendment-2, aviation gasoline, and AN-F-28 plus 2 percent xylidines by weight. Tests were run at a compression ratio of 7.0 with inlet-air temperatures of 150 F and 250 F and at a compression ratio of 8.0 with an inlet-air temperature of 250 F. All other engine conditions were held constant. The piston-head temperature was varied by circulation of oil through passages in the crown of a liquid-cooled piston. This method of piston cooling decreased the piston-head temperature about 80 F. The data are not intended to constitute a recommendation as to the advisability of piston cooling in practice.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-WR-E-35 , NACA-ARR-E4G13
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  • 37
    Publication Date: 2019-07-11
    Description: The wide use of diffusers, in various fields of technology, has resulted in several experimental projects to study the action and design of diffusers. Most of the projects dealt with steam (steam turbine nozzles). But diffusers have other applications - that is, ventilators, smoke ducts, air coolers, refrigeration, drying, and so forth. At present there is another application for diffusers in wind-tunnel design. Because of higher requirements and increased power of such installations more attention must be paid to the correctness of work and the decrease in losses due to every section of the tunnel. A diffuser, being one of the component parts of a tunnel , can in the event of faulty construction introduce considerable losses. Therefore, in the design of the new CAHI wind tunnel, it was suggested that an experimental study of diffusers be made, with a view to applying the results to wind tunnels. The experiments conducted by K. K. Baulin in the laboratories of CAHI upon models of diffusers of different cross sections, lengths, and angles of divergence, were a valuable source of experimental data. They were of no help, however, in reaching any conclusion regarding the optimum shape because of the complexity and diversity of the factors which all appeared simultaneously, thereby precluding the.study of the effects of any one factor separately. On the suggestion of the director of the CAHI,Prof. B. N. Ureff, it was decided to experiment on a two-dimensional diffuser model and determine the effect, of the angle of divergence. The author is acquainted with two experimental projects of like nature: the first was conducted with water, the other with air. The first of these works, although containing a wealth of experimental data, does not indicate the nature of flow or its relation to the angle of divergence. The second work is limited to four angles - that is, 12 deg, 24 deg, 45 deg, 90 deg. The study of this diffuser did not supply any information about the effect of smaller angles which, because of their advantages, are more commonly used, The author was able to acquaint himself with the second work only after the experiments were started. For these reasons, as well as because on the basis of those works no conclusion can be reached regarding the nature of flow distribution, of eddies, and so forth, experimental work was continued. The need for determining flow patterns follows from the fact that from them are determined methods of measurement - that is, the determination of velocities by means of the pitot tube, which, as is well known, gives correct indications only when placed with its axis parallel to the axis of flow. The data contained in this report were obtained from experiments conducted by the Aerodynamical Laboratories of the CAHI. The solutions to some. of the mathematical problems connected with the experiments are due to Prof. S. A, Chapligin.
    Keywords: Aerodynamics
    Type: NACA-TM-1059 , Report of the Central Aero-Hydrodynamical Inst., Moscow; Rept-21
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  • 38
    facet.materialart.
    Unknown
    In:  CASI
    Publication Date: 2019-07-11
    Description: In the present report the theory of free turbulence propagation and the boundary layer theory are developed for a plane-parallel free stream of a compressible fluid. In constructing the theory use was made of the turbulence hypothesis by Taylor (transport of vorticity) which gives best agreement with test results for problems involving heat transfer in free jets.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1058 , Report of the Central Aero-Hydrodynamical Inst., Moscow; Rept-377
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  • 39
    Publication Date: 2019-07-11
    Description: Detail calculations are presented of the shifts in stick-fixed neutral point of the Republic XF-12 airplane due to the windmilling propellers and to the fuselage. The results of these calculations differ somewhat from those previously made for this airplane by Republic Aviation Corporation personnel under the direction of Langley flight division personnel. Due to these differences the neutral point for the airplane is predicted to be 37.8 percent mean aerodynamic chord, instead of 40.8 percent mean aerodynamic chord as previously reported.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-CMR-L4J16
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  • 40
    Publication Date: 2019-06-28
    Description: The relation between the elevator hinge moment parameters and the control forces for changes in forward speed and in maneuvers is shown for several values of static stability and elevator mass balance. The stability of the short period oscillations is shown as a series of boundaries giving the limits of the stable regions in terms of the elevator hinge moment parameters. The effects of static stability, elevator moment of inertia, elevator mass unbalance, and airplane density are also considered. Dynamic instability is likely to occur if there is mass unbalance of the elevator control system combined with a small restoring tendency (high aerodynamic balance). This instability can be prevented by a rearrangement of the unbalancing weights which, however, involves an increase of the amount of weight necessary. It can also be prevented by the addition of viscous friction to the elevator control system provided the airplane center of gravity is not behind a certain critical position. For high values of the density parameter, which correspond to high altitudes of flight, the addition of moderate amounts of viscous friction may be destabilizing even when the airplane is statically stable. In this case, increasing the viscous friction makes the oscillation stable again. The condition in which viscous friction causes dynamic instability of a statically stable airplane is limited to a definite range of hinge moment parameters. It is shown that, when viscous friction causes increasing oscillations, solid friction will produce steady oscillations having an amplitude proportional to the amount of friction.
    Keywords: Aircraft Stability and Control
    Type: AD-A301267 , NACA-TR-791
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  • 41
    Publication Date: 2019-06-28
    Type: NACA-TN-949
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  • 42
    Publication Date: 2019-06-28
    Type: NACA-TN-984
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  • 43
    Publication Date: 2019-06-28
    Type: NACA-TN-931
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  • 44
    Publication Date: 2019-06-28
    Description: Flat sheet panels of aluminum alloy (all 17S-T except for two specimens of 24S-T) were tested under normal pressures with clamped edge supports in the structures laboratory of the Guggenheim Aeronautical Laboratory, California Institute of Technology. The thicknesses used ranged from 0.010 to 0.080 inch; the panel sizes ranged from 10 by 10 inches to 10 by 40 inches; and the pressure range was from 0 to 60-pounds-per-square-inch gage. Deflection patterns were measured and maximum tensile strains in the center of the panel were determined by electric strain gages. The experimental data are presented by pressure-strain, pressure-maximum-deflection, and pressure-deflection curves. The results of these tests have been compared with the corresponding strains and deflections as calculated by the simple membrane theory and by large deflection theories.
    Type: NACA-TN-943
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  • 45
    Publication Date: 2019-06-28
    Description: Numerical methods have been developed for obtaining the steady, adiabatic flow field of a frictionless, perfect gas about arbitrary two-dimensional bodies. The solutions include the subsonic velocity regions, the supersonic velocity regions, and the transition compression shocks, if required. Furthermore, the rotational motion and entropy changes following shocks are taken into account. Extensive use is made of the relaxation method. In this report the details of the methods of solution are emphasized so as to permit others to solve similar problems. Solutions already obtained are mentioned only by way of illustrating the possibilities of the methods described. The methods can be applied directly to wind tunnel and free air tests of arbitrary airfoil shapes at subsonic, sonic, and supersonic speeds.
    Type: NACA-TN-932
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  • 46
    Publication Date: 2019-06-28
    Description: In the present part I of a series of reports on the inward bulge type buckling of monocoque cylinders the buckling load in combined bending and compression is first derived. Next the reduction in the buckling load because of a nonlinear direct stress distribution is determined. In experiments nonlinearity may result from an inadequate stiffness of the end attachments in actual airplanes from the existence of concentrated loads or cut-outs. The effect of a shearing force upon the critical load is investigated through an analysis of the results of tests carried out at GALCIT with 55 reinforced monocoque cylinders. Finally, a simple criterion of general instability is presented in the form of a buckling inequality which should be helpful to the designer of a monocoque in determining the sizes of the rings required for excluding the possibility of inward bulge type buckling.
    Type: NACA-TN-938
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  • 47
    Publication Date: 2019-06-28
    Description: A solution of Von Karman's fundamental equations for plates with large deflections is presented for the case of a shear web divided into square panels by reinforcing struts. Numerical solutions are given for struts of infinite rigidity and for struts the weight of which is one-fourth the weight of the sheet. The results are compared with Wagner's diagonal tension theory as extended by Kuhn and by Langhaar. It is found that the diagonal tension theory as developed by Kuhn agrees best with the present paper in the practical range when r=1/4. Kuhn's theory is in especially good agreement for the force in the strut when r=1/4.
    Type: NACA-TN-962
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  • 48
    Publication Date: 2019-06-28
    Description: General thin-airfoil theory for a compressible fluid is formulated as boundary problem for the velocity potential, without recourse to the theory of vortex motion. On the basis of this formulation the integral equation of lifting-surface theory for an incompressible fluid is derived with the chordwise component of the fluid velocity at the airfoil as the function to be determined. It is shown how by integration by parts this integral equation can be transformed into the Biot-Savart theorem. A clarification is gained regarding the use of principal value definitions for the integral which occur. The integral equation of lifting-surface theory is used a s the starting point for the establishment of a theory for the nonstationary airfoil which is a generalization of lifting-line theory for the stationary airfoil and which might be called "lifting-strip" theory. Explicit expressions are given for section lift and section moment in terms of the circulation function, which for any given wing deflection is to be determined from an integral equation which is of the type of the equation of lifting-line theory. The results obtained are for airfoils of uniform chord. They can be extended to tapered airfoils. One of the main uses of the results should be that they furnish a practical means for the analysis of the aerodynamic span effect in the problem of wing flutter. The range of applicability of "lifting-strip" theory is the same as that of lifting-line theory so that its results may be applied to airfoils with aspect ratios as low as three.
    Type: NACA-TN-946
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  • 49
    Publication Date: 2019-06-28
    Description: This paper is the second part of a series of reports on the inward bulge type buckling of monocoque cylinders. It presents the results of an experimental investigation of buckling in combined bending and compression. In the investigation it was found that the theory developed in part I of the present series predicts the buckling load in combined bending and compression with the same degree of accuracy as the older theory does in pure bending. In the realm covered by the experiments no systematic variation of the parameter N was observed. The analysis of the test results afforded a check on the theories of buckling of a curved panel. The agreement between experiment and theory was reasonably good. In addition, the effect of the end conditions upon the stress distribution under loads and upon initial stresses was investigated.
    Type: NACA-TN-939
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  • 50
    Publication Date: 2019-06-28
    Description: It is well known that the vorticity for any fluid element is constant if the fluid is non-viscous and the change of state of the fluid is isentropic. When a solid body is placed in a uniform stream, the flow far ahead of the body is irrotational. Then if the flow is further assumed to be isentropic, the vorticity will be zero over the whole filed of flow. In other words, the flow is irrotational. For such flow over a solid body, it is shown by Theodorsen that the solid body experiences no resistance. If the fluid has a small viscosity, its effect will be limited in the boundary layer over the solid body and the body will have a drag due to the skin friction. This type of essentially isentropic irrotational flow is generally observed for a streamlined body placed in a uniform stream, if the velocity of the stream is kept below the so-called "critical speed." At the critical speed or rather at a certain value of the ratio of the velocity of the undisturbed flow and the corresponding velocity of sound, shock waves appear. This phenomenon is called the "compressibility bubble." Along a shock wave, the change of state of the fluid is no longer isentropic, although still adiabatic. This results in an increase in entropy of the fluid and generally introduces vorticity in an originally irrotational flow. The increase in entropy of the fluid is, of course, the consequence of changing part of the mechanical energy into heat energy. In other words, the part of fluid affected by the shock wave has a reduced mechanical energy. Therefore, with the appearance of shock waves, the wake of the streamline body is very much widened, and the drag increases drastically. Furthermore, the accompanying change in the pressure distribution over the body changes the aerodynamic moment acting on it and in the case of an airfoil decreases the lift force. All these consequences of the breakdown of isentropic irrotational flow are generally undesirable in applied aerodynamics. Its occurrence should be delayed as much as possible by modifying the shape or contour of the body. However, such endeavor will be very much facilitated if the cause or the criterion for the breakdown can be found first.
    Type: NACA-TN-961
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