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  • Aircraft Design, Testing and Performance  (14)
  • 42.75  (6)
  • 1950-1954  (20)
  • 1953  (20)
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  • 1950-1954  (20)
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  • 1
    Publication Date: 2014-07-15
    Description: A method has been proposed for predicting the effect of a rapid blade-pitch increase on the thrust and induced-velocity response of a helicopter rotor. General equations have been derived for the ensuing motion of the helicopter. These equations yield time histories of thrust, induced velocity, and helicopter vertical velocity for given rates of blade-pitch-angle changes and given rotor-angular-velocity time histories. The results of the method have been compared with experimental results obtained with a rotor mounted on the Langley helicopter test tower. The calculated and experimental results are in good agreement, although, in general, the calculated thrust-coefficient overshoots are about 10 percent greater than those obtained experimentally.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-3044
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  • 2
    facet.materialart.
    Unknown
    In:  Zoologische Mededelingen (0024-0672) vol.32 (1953) nr.9 p.87
    Publication Date: 2013-03-01
    Description: I have to thank Dr. H. C. Blöte of the Leiden Museum of Natural History for his kindness to entrust me with a number of Carabidae from Indonesia for identification. A few species appear to be new to science; the descriptions follow below. One genus, Horniulus Jedl., is new to the whole of the Malay Archipelago, and another, Bembidion Latr., is new to Sumatra. Of the latter genus there are already a couple of species known from Java. I am much obliged to Mr. E. B. Britton of the British Museum, who carefully compared a few species with specimens in the collections of the British Museum and in Andrewes' collections. The type specimens are in the Leiden Museum. Oxygnathopsis gen. nov. (fig. 1 f) (Andrewes (1938, p. 196) described Oxygnathus javanus upon a single specimen from Java. With regard to the proper genus Andrewes was not absolutely sure because of a number of important differences, but before introducing a new genus he preferred to wait till more material was available. In the sending of the Leiden Museum I found a second specimen, which shows the same characteristics as the specimen described by Andrewes, so that in my opinion a new genus is desirable. The two genera are to be distinguished as follows: 1 (2) Head with the clypeus bisetose, two setae on each side over the eyes, facial carinae and sulci present; prothorax with two lateral setae on each side. Range: Assam and Burma.........Oxygnathus Dej. 2 (1) Clypeus without setae, one supra-orbital seta, the front seta is wanting, no facial Fig. 1. a, Coptodera flavipes sp. n., left elytron; b, Horniulus quadrimaculatus sp. n.,
    Keywords: 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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  • 3
    facet.materialart.
    Unknown
    In:  Zoologische Mededelingen (0024-0672) vol.32 (1953) nr.3 p.31
    Publication Date: 2013-03-01
    Description: Eine Bestimmungssendung des Deutschen Entomologischen Institutes veranlasste mich, die Systematik der asiatischen Coenochilus zu studieren. Die Museen Leiden, Berlin und München und die Herren Frey, Haberäcker, Klapperich und van Nidek stellten mir ihr Material zur Verfügung; Herr Reichert des Museums Dresden und Herr Ruter des Museums Paris gaben bereitwillig Auskunft über Typen ihrer Museen. Ihnen alien sowie den Herren Prof. Dr. Sachtleben, Prof. Dr. Delkeskamp, Dr. C. de Jong, Dr. H. C. Blöte, Dr. Forster, H. Freude, P. Müller und St. von Breuning danke ich bestens für ihre Hilfe. Als Ergebnis meiner Studien veröffentliche ich hier die Beschreibung zweier neuer Arten und des ♂ von C. leopoldi Bourg. sowie eine aus der Arrow'schen Tabelle in der Fauna of British India weiterentwickelte Bestimmungstabelle aller asiatischen Arten. 1. Der Katalog von Junk-Schenkling Pars 72 aus 1921 ist auf Seite 366 f. durch folgende Arten zu ergänzen: assmuthi Wasmann, Wiener Ent. Zeit., vol. 37, 1918, S. 19. bifoveolatus Fairmaire, Ann. Soc. Ent. Fr., 1888, S. 344. leopoldi Bourgoin, Mem. Mus. Roy. H.N. Belg., 1933, Voyage Leopold, vol. IV fasc. 9, Col. II, S. 31. leveillei Nonfried, Berl. Ent. Zeit., 1891, S. 372, der nach Arrow kein Pilinurgus ist. obesus Wasmann, Wiener Ent. Zeit., vol. 37, 1918, S. 21. obscurus Westwood, Tijdsch. v. Ent., vol. 26, 1883, S. 62-65. platycerus Gerstäcker, von S. 368 des Kat. (1883). sumatranus Westwood, Tijdsch. v. Ent., vol. 26, 1883, S. 62-65. uncinatipes Moser, D. Ent. Zeit., 1915, S. 596.
    Keywords: 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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  • 4
    Publication Date: 2013-03-01
    Description: Contents ι. Introduction..............I 2. Systematics (a, The correct name of the genus p. 4; b, Diagnostic characters of the species and subspecies p. 6; c, Abbreviations p. 9; d, Key to the species and subspecies p. 10; e, Survey of the species and subspecies p. 11; f, Disregarded specimens p. 30; g, Wilcoxon tests for the difference between certain measurements in allied subspecies p. 31; h, Early stages p. 36; i, The species concept in Nyctalemon p. 37).......... 3. Biology............... 38 4. Distribution.............. 43 5. Evolution............... 46 6. Bibliography.............. 52 1. INTRODUCTION In November 1949 the late Professor Dr. L. J. Toxopeus of Bandung, Java, sent me a specimen of Nyctalemon for identification, but neither with the help of our collection, nor with the current literature did I succeed in ascertaining the correct name of this insect. On the contrary it appeared that, though the described forms of this genus clearly were of different value, viz., partly good species, partly geographical subspecies representing these species in restricted areas, no satisfactory division of the genus into species and subspecies had been given. Thus, Seitz' classification of the known forms into four species of which three are polytypic proved to make no sense. Therefore I resolved to study the genus more closely. In the ensuing correspondence Toxopeus gave me the benefit of his experience by providing references to relevant literature and quotations from
    Keywords: 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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  • 5
    facet.materialart.
    Unknown
    In:  Zoologische Mededelingen (0024-0672) vol.32 (1953) nr.18 p.203
    Publication Date: 2013-03-01
    Description: COPROMORPHIDAE Meyrick, 1905, Journ. Bombay Nat. Hist. Soc, vol. 16, p. 606. This small family represents a natural group with clearly marked characters, and is easy of descrimination. It inhabits tropical regions of Asia and extends through the Papuan region over the whole Pacific. The last mentioned region might be the country of origin of this group, as genera with peculiar and possibly archaic characters have been recorded from the Pacific Islands; some of those species are distinguished by an exceptionally large size. One of the interesting points with regard to the family is its possible place in the system. The long-ciliate or pectinate antennae, the neuration, and the complicated genital apparatus of the male seem to indicate an affinity with the Tineoidea. The general facies, however, is divergent to some extent, while the presence of a cubital pecten on the hind wings fundamentally discriminates this family from all the Tineoidea sensu stricto. When describing the family, Meyrick suggested that the cubital pecten might point towards an affinity with the Tortricoidea ; this relation, however, is not supported by any other characters. He further surmised that the Copromorphidae would be nearest allied to the Xyloryctidae ; in my opinion this surmise is devoid of any ground. Later Meyrick tried to combine with the Copromorphidae two other groups of "Tineina" that also are in possession of a cubital pecten, viz., the family Orneodidae, and the genus Hypertropha Meyr. The relation of the former with the Copromorphidae, however, is problematic, and deserves further proofs, while Hypertropha has in my opinion nothing in common with the family concerned, except for the
    Keywords: 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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  • 6
    facet.materialart.
    Unknown
    In:  Zoologische Mededelingen (0024-0672) vol.32 (1953) nr.5 p.43
    Publication Date: 2013-03-01
    Description: Some time ago I was asked to identify a fossil coleopteron which had been found in the drill cuttings of an oil well in the Southern part of Sumatra. As the fossil is only a few millimetres long it may be mentioned as an amazing fact that so small an object has been found during rather rough work like oil drilling. The details of the locality as given by Mr. A. Wright Jr. of the N.V. Standard-Vacuum Petroleum Maatschappij are as follows: "The well is one of our Kaja wells, a wildcat well located 3.3 kilometres N. 300 E. from the northeast edge of the Djirah oilfield. The drill cutting was obtained from a depth of 1930 feet subsea. Although, in drill cuttings, there is a certain measure of uncertainty as to the exact level of derivation, we have sufficient evidence to be sure that the fossil actually derives from this depth. The age is Tertiary-e; it occurs below beds of Baturadja stage age, but 200 feet above a lepidocyclina-bearing horizon. The fossil occurs in a shale interval of a formation which is generally non-fossiliferous; conditions were presumably marine, but either oligotrophe or toxic; the water at the time of deposition was shallow." The fossil is pyritized, dark bronze-greyish in colour. It is nearly free from substrate, though in some crevices a light grey, rather soft, somewhat fattish substance is found which can be taken away rather easily. The fossil was sent to the Rijksmuseum van Natuurlijke Historie at Leiden, mounted in a small box on a slide, pasted to the bottom with tragacanth. During the studies it was left in the small box, and kept in an exsiccator to preserve the fossil against deterioration by atmospheric influence.
    Keywords: 42.75
    Repository Name: National Museum of Natural History, Netherlands
    Type: Article / Letter to the editor
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  • 7
    facet.materialart.
    Unknown
    In:  Zoologische Mededelingen (0024-0672) vol.32 (1953) nr.6 p.49
    Publication Date: 2013-03-01
    Description: I. Attacus dohertyi dammermani nov. subspec. (Plate II) Large, apex of fore wing moderately produced, general coloration of wings, head, notum including patagia, and abdomen rather light reddish brown, several intersegmental folds between the abdominal tergites blackish. In both wings the terminal area somewhat lighter, more yellowish brown, in apex of fore wing grading into yellowish. Hind wing with the apical area markedly reddish. In fore wing the dark apical spot and red dash weak, submarginal line practically wanting, in hind wing a somewhat undulating submarginal dark line well developed. Postmedian band in both wings strongly serrate, but not bent inwards. Antemedian band in both wings less distinct, not serrate, in fore wing angled on base of v2, in hind wing curved inwards. The vitreous patches in both wings very large, guttiform by having the base curved outwards, the basal angles rounded, and the top elongated and pointed towards the postmedian band. In both wings with two additional vitreous patches which are in fore wing slightly larger than in hind wing. In hind wing the lower patch communicates with the interior black border of the postmedian band. All these spots bordered by a black margin. The interior orange yellow border, so obvious in many dohertyi specimens, is wanting or indicated by some inconspicuous traces only. Underside corresponding with upperside, the outer half very light, as in atlas, but the subterminal markings in both wings practically wanting or obsolete. Lateral markings of abdomen much less developed than in atlas. I ♀, 25 cm, holotype, W. Sumba, IV. 1925, labelled Dammerman, Sumba Exp., in Museum Leiden. 2. THE SPECIES OF THE GENUS Attacus L. IN THE FAR EAST.
    Keywords: 42.75
    Repository Name: National Museum of Natural History, Netherlands
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  • 8
    Publication Date: 2019-07-11
    Description: A free-flight 0.12-scale rocket-boosted model of the North American MX-770 (X-10) missile has been tested in flight by the Pilotless Aircraft Research Division of the Langley Aeronautical Laboratory. Drag, longitudinal stability, and duct performance data were obtained at Mach numbers from 0.8 to 1.7 covering a Reynolds number range of about 9 x 10(exp 6) to 24 x 10(exp 6) based on wing mean aerodynamic chord. The lift-curve slope, static stability, and damping-in-pitch derivatives showed similar variations with Mach number, the parameters increasing from subsonic values in the transonic region and decreasing in the supersonic region. The variations were for the most part fairly smooth. The aerodynamic center of the configuration shifted rearward in the transonic region and moved forward gradually in the supersonic region. The pitching effectiveness of the canard control surfaces was maintained throughout the flight speed range, the supersonic values being somewhat greater than the subsonic. Trim values of angle of attack and lift coefficient changed abruptly in the transonic region, the change being associated with variations in the out-of-trim pitching moment, control effectiveness, and aerodynamic-center travel in this speed range. Duct total-pressure recovery decreased with increase in free-stream Mach number and the values were somewhat less than normal-shock recovery. Minimum drag data indicated a supersonic drag coefficient about twice the subsonic drag coefficient and a drag-rise Mach number of approximately 0.90. Base drag was small subsonically but was about 25 percent of the minimum drag of the configuration supersonically.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL53D10A
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  • 9
    Publication Date: 2019-07-11
    Description: An investigation was made to determine the static longitudinal and lateral stability and control characteristics of a l/6-scale model of the revised Republic XF-84H airplane with and without the propeller operating. The model had a 40deg swept wing of aspect ratio 3.45 and was equipped with a thin, three-blade supersonic-type propeller. Modifications incorporated in the revised model included a raised horizontal tail, increased rudder size, wing fences at 65 percent semispan, and a modified wing leading edge outboard of the fences. The test results for flap-retracted and flap-deflected conditions indicated that the revised configuration should be satisfactory for most normal flight conditions provided the angle of attack does not exceed the angle for pitch-up. An abrupt pitch-up tendency of the model was evident for the zero thrust condition above approximately 15' angle of attack. Although the effects of power were destabilizing, power-on longitudinal stability was satisfactory through the angle-of-attack range for which the model was stable with zero thrust. Above the angle of attack for pitch-up, an uncontrollable left roll-off tendency would be expected with power on and slats retracted. Projection of wing slats or use of leading-edge chord-extensions with only the left extension drooped were found beneficial in controlling the roll-off tendency with power on; however the most effective means found was projection of only the left slat.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL53I24
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  • 10
    Publication Date: 2019-06-28
    Description: Pressure-distribution measurements have been made on the fus elage of the Bell X- 1 research airplane. Data are presented for angles of attack from 2 deg. to 8 deg. during pull-ups at Mach numbers of about 0.78, 0.85, 0.88, and 1.02. The results of the investigation indicated that a large portion of the load carried by the fuselage was in the vicinity of the wing and may be attributed to wing-to-fuselage carryover. The presence of the wing from the 41 to 60 percent fuselage stations influenced the fuselage pressures from about 30 to 65 percent fuselage length at Mach numbers of approximat ely 0.78, 0.85, and 0.88, and from about 35 to 80 percent fuselage length at a Mach number of approximately 1.02. The fuselage contributed about 20 percent of the total airplane normal-force coefficient. The center of pressure of the fuselage load throughout the tests was located from 41 to 51 percent fuselage length, which corresponds to the forward half of the wing root-chord location.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L53I15
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  • 11
    Publication Date: 2019-07-12
    Description: An investigation has been made at high subsonic speeds of the aerodynamic'characteristics in pitch and sideslip of a l/l4-scale model of the Grumman XF10F airplane with a wing sweepback angle of 42.5. The longitudinal stability characteristics (with the horizontal tail fixed) indicate a pitch-up near the stall; however, this was somewhat alleviated by the addition of fins to the side of the fuselage below the horizontal tail. The original model configuration became directionally unstable for small sideslip angles at Mach numbers above 0.8; however, the instability was eliminated by several different modifications.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL53G20
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  • 12
    Publication Date: 2019-07-12
    Description: A limited investigation of a 1/24-scale dynamically similar model of the Navy Bureau of Aeronautics DR-77 design was conducted in Langley tank no. 2 to determine the calm-water take-off and the rough-water landing characteristics of the design with particular regard to the take-off resistance and the landing accelerations. During the take-off tests, resistance, trim, and rise were measured and photographs were taken to study spray. During the landing tests, motion-picture records and normal-acceleration records were obtained. A ratio of gross load to maximum resistance of 3.2 was obtained with a 30 deg. dead-rise hydro-ski installation. The maximum normal accelerations obtained with a 30 deg. dead-rise hydro-ski installation were of the order of 8g to log in waves 8 feet high (full scale). A yawing instability that occurred just prior to hydro-ski emergence was improved by adding an afterbody extension, but adding the extension reduced the ratio of gross load to maximum resistance to 2.9.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL53F04
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  • 13
    Publication Date: 2019-07-11
    Description: An experimental investigation has been conducted to determine the dynamic stability and control characteristics of a 0.13-scale free-flight model of the Convair XFY-1 airplane in test setups representing the setup proposed for use in the first flight tests of the full-scale airplane in the Moffett Field airship hangar. The investigation was conducted in two parts: first, tests with the model flying freely in an enclosure simulating the hangar, and second, tests with the model partially restrained by an overhead line attached to the propeller spinner and ground lines attached to the wing and tail tips. The results of the tests indicated that the airplane can be flown without difficulty in the Moffett Field airship hangar if it does not approach too close to the hangar walls. If it does approach too close to the walls, the recirculation of the propeller slipstream might cause sudden trim changes which would make smooth flight difficult for the pilot to accomplish. It appeared that the tethering system proposed by Convair could provide generally satisfactory restraint of large-amplitude motions caused by control failure or pilot error without interfering with normal flying or causing any serious instability or violent jerking motions as the tethering lines restrained the model.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL54B16A
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  • 14
    Publication Date: 2019-07-12
    Description: Static tests on a segment of a transpiration-cooled turbine rotor blade with a wire-cloth shell were conducted to determine the flow coefficients associated with some representative metering orifices. Average flow coefficients from 0.96 to 0.79 were obtained for orifices of 0.031 to 0.102 inch diameter.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E53L30a
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  • 15
    Publication Date: 2019-07-11
    Description: An experimental investigation has been made in the Langley stability tunnel at low speed to determine the static longitudinal and lateral stability characteristics of a l/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient were investigated for the complete model and for certain components of the model. Effects of control deflections and of propeller-blade angle were investigated briefly for the complete model. Most of the tests were made through an angle-of-attack range from about -4 deg. to 29 deg, and the thrust-coefficient range was from 0 t o 0.7. In order to expedite distribution of these data to interested persons, no analysis of the data has been prepared for this report,
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL53B20
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  • 16
    Publication Date: 2019-07-11
    Description: An application of airfoil design methods was used to design series of related turbine-blade profiles to satisfy the conditions of inlet flow angle and turning angle encountered in the usual range of turbine operation. A series of blade profiles applicable to most turbine blading requirements and a secondary series with particular reference to impulse conditions were designed. Five blade sections from these series ranging in mean-line turning angles from 63 deg. to 120 deg. were tested in low-speed cascade tunnels. From low-speed test results optimum blade angles of attack were selected at each test condition. The induced angle and the deviation angle of the flow were determined from the low-speed data. If these angles are known for the solidity and inlet angle of an application, the necessary camber is specified. A method of predicting high-speed pressure distributions from low-speed cascade test results is presented to extend the usefulness of the low-speed data. Sample high-speed tests of two of the five blade sections were made at Mach numbers up to the critical value. The results indicated satisfactory flow conditions in all of the blade passages tested.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L53G15
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  • 17
    Publication Date: 2019-07-11
    Description: An investigation has been made in the Langley 9- by 12-inch supersonic blowdown tunnel to determine the effects of external-store location on the lift, drag, and pitching-moment characteristics of a 45 degree sweptback wing at Mach numbers of 1.41, 1.62, and 1.96. The spanwise, chordwise, and vertical location of a Douglas-Aircraft Company, Inc., store of fineness ratio 8.58 was systematically varied over the outer 60 percent of the wing semispan. A brief investigation of strut sweep angle was also made. The test Reynolds number based on the wing mean aerodynamic chord ranged from 1.3 x 10(exp 6) to 1.5 x 10(exp 6).
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L52J27
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  • 18
    Publication Date: 2019-07-11
    Description: The hydrodynamic characteristics of a preliminary design of the Martin XP6M-1 flying boat have been determined. Longitudinal stability during take-off and landing, resistance of the complete model, and behavior during taxiing and landing in rough water are presented.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-SL53K06
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  • 19
    Publication Date: 2019-07-11
    Description: Preliminary results of one phase of a control-motion study program involving several jet fighter-type airplanes are presented in time-history form and are summarized as maximum measured quantities plotted against indicated airspeed. The results pertain to approximately 1,000 maneuvers performed by a Republic F-84G jet-fighter airplane during squadron operational training. The data include most tactical maneuvers of which the F-84G airplane is capable. Maneuvers were performed at pressure altitudes of 0 to 30,000 feet with indicated airspeeds ranging from the stalling speed to approximately 515 knots.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L53C27
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  • 20
    Publication Date: 2019-08-28
    Description: A systematic research program is being carried out in the Langley high-speed 7- by 10-foot tunnel to determine the aerodynamic characteristics of various arrangements of the component parts of research-type airplane models, including some complete model configurations. Data are being obtained on characteristics in pitch, sideslip, and during steady roll at Mach numbers from 0.40 to about 0.95. This paper presents results which show the effect of taper ratio on the aerodynamic characteristics in sideslip of wing-fuselage combinations having wings with a sweep of 45 degrees at the quarter-chord line, an aspect ratio of 4, and a NACA 65A006 airfoil section.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-L53B25a
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