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  • Aerodynamics  (20)
  • Forst  (3)
  • 1985-1989
  • 1980-1984
  • 1940-1944  (23)
  • 1944  (23)
  • 1
    facet.materialart.
    Unknown
    In:  Anz. Schädl.kunde 20: 16ff
    Publication Date: 1944
    Description: Beziehung zwischen Klima und Insektenbiologie KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Deutschland, teilw. einzelne Regionen ; 1936-1941 ; Insekten ; Luftfeuchte ; Forst ; Klima ; Niederschlag ; Pflanzenschädling ; Temperatur
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  • 2
    facet.materialart.
    Unknown
    In:  Forstwiss. Centralbl. Thar. forstl. Jahrb. 66: 115-120
    Publication Date: 1944
    Description: Beschreibung des Ertragsrückgang und der Schäden durch die Spätfröste im Mai 1943 KATASTER-BESCHREIBUNG: Spätfröste verursachten Schäden an Kiefern, Maitriebbildung teilweise extrem gestört und Posthorn- oder kandelaberartige Triebbildung als Folge des Frostes, unterschiedliche Empfindlichkeit der Baumarten KATASTER-DETAIL: Delta T -, (Ende Mai 〈 -6°C), dann schwere Schäden an Walnuss, Eiche, Robinie, Roteiche, Esche, Tanne, mittlere Schiiden:Buche, Roterle, Ahorn, Fichte, Douglasie, Lärche; geringe Schiiden: Roflkastanie,Hainbuche, Linde, Weisserle, Ulme, Birke. Im allgemeinen blieben ohne Schäden: Aspe, Eberesche, Traubenkirsche, Kiefer, Strobe und Bankskiefer.
    Keywords: Nordostdeutschland ; 1943 ; Buche ; Eiche ; Ertrag ; Fichte ; Forst ; Kiefer ; Roterle ; Frost ; Ulme ; Rosskastanie
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  • 3
    facet.materialart.
    Unknown
    In:  Anz. Schädl.kunde 20: 13-16
    Publication Date: 1944
    Description: Beschreibung zum Befall von kanadischen Pappeln mit dem Prachtkäfer KATASTER-BESCHREIBUNG: KATASTER-DETAIL:
    Keywords: Rheinland-Pfalz ; 1934-1943 ; Insekten ; Forst ; Pflanzenschädling
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  • 4
    Publication Date: 2019-06-28
    Description: An investigation was made of the flow downstream from a "two-dimensional" grid formed of parallel rods. In both two and three dimensional jet fields there is a critical range of grid density below which the downstream flow is stable and above which it is unstable. The flow can be completely stabilized by means of an adequate lateral contraction beginning immediately after the grid or by use of a fine-mesh damping screen parallel to the grid plane and within a definite range of positions downstream from the grid.
    Keywords: Aerodynamics
    Type: NACA-WR-W-90 , NACA-ACR-4H24
    Format: application/pdf
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  • 5
    Publication Date: 2019-06-28
    Description: Pressure distribution measurements were made over an airfoil with slotted Frise aileron up to 0.76 Mach at various angles of attack and aileron defections. Section characteristics were determined from these pressure data. Results indicated loss of aileron rolling power for deflections ranging from -12 Degrees to -19 Degrees. High stick forces for non-differential deflections incurred at high speed, which were due to overbalancing tendency of up-moving aileron, may precipitate serious control difficulties. Detailed results are presented graphically.
    Keywords: Aerodynamics
    Type: NACA-WR-L-266 , NACA-ACR-L4G12
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  • 6
    Publication Date: 2019-06-28
    Description: Methods are given of determining the potential flow plast an arbitrary cascade of airfoils and the inverse problem of determining an airfoil having a prescribed velocity distribution in cascade. Results indicated that Cartesian mapping function method may be satisfactorily extended to include cascades. Numerical calculation for computing cascades by Cartesian mapping function method is considerably greater than for single airfoils but much less than hitherto required for cascades. Detailed results are presented graphically.
    Keywords: Aerodynamics
    Type: NACA-WR-L-81 , NACA-ARR-L4K22B
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  • 7
    Publication Date: 2019-06-28
    Description: Flight tests were conducted on the OS2U-2 seaplane with simple circular-arc-type ailerons directly connected to the actuating torque tube. Two aileron test installations were made, differing only in the inclination of the projecting surface with the wing's upper surface. The lateral-control characteristics of the airplane were determined from data obtained in stalls and rudder-fixed aileron rolls. The revised ailerons were deficient in maximum rolling effectiveness, but were capable of controlling the rolling tendencies of the airplane near the stall.
    Keywords: Aerodynamics
    Type: NACA-WR-A-32
    Format: application/pdf
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  • 8
    Publication Date: 2019-06-28
    Description: Tank tests were made of a hull model of the Hughes-Kaiser cargo airplane for estimates of take-off performance and maximum gross load for take-off. At hump speeds, with the model free to trim, the trim and resistance were high, which resulted in a load-resistance ratio of approximately 4.0 for a gross load coefficient of 0.75. With a 4000,000-lb load, the full size craft may take off in 69 sec over a distance of 5600 ft.
    Keywords: Aerodynamics
    Type: NACA-WR-L-683
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  • 9
    Publication Date: 2019-06-28
    Description: Results of flight tests indicate that profile-drag coefficients which were obtained with the low-drag airfoils were lower than with the conventional types over the range of light coefficients tested. For comparable conditions of the lift coefficient and Reynolds Number, the low-drag airfoils have profile-drag coefficients which may be 27 percent lower than the profile drag of the conventional airfoils tested. Detailed results are presented graphically.
    Keywords: Aerodynamics
    Type: NACA-WR-L-139 , NACA-ACR-L4E31
    Format: application/pdf
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  • 10
    Publication Date: 2019-06-28
    Description: Rough conventional, smooth conventional, and laminar-flow or low-drag sections were tested. The items covered are rotor thrust for fixed power in hovering, range and endurance at cruising speed, and power required at high-forward speed. Calculations indicated that a smooth conventional section gives marked performance gains. Smaller gains are obtainable by using a low-drag section. At high speeds or loads the low-drag section is inferior to the smooth conventional section.
    Keywords: Aerodynamics
    Type: NACA-WR-L-26 , NACA-ACR-L4H05
    Format: application/pdf
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  • 11
    Publication Date: 2019-06-28
    Description: An investigation was made of the cooling characteristics of a P and W R-2800 engine with NACA short-nose high inlet-velocity cowling. The internal aerodynamics of the cowling were studied for ranges of propeller-advance ratio and inlet-velocity ratio obtained by deflection of cowling flaps. Tests included variations of engine power, fuel/air ratio and cooling-air pressure drop. Engine cooling data are presented in the form of cooling correlation curves, and an example for calculation of cooling requirements in flight is included.
    Keywords: Aerodynamics
    Type: NACA-WR-L-207 , NACA-ACR-L4F06
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  • 12
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aerodynamics
    Type: NACA-WR-L-318 , NACA-ARR-4A26
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  • 13
    Publication Date: 2019-06-28
    Description: Results are presented for tests of two wings, an NACA 230-series wing and a highly-cambered NACA 66-series wing on a twin-engine pursuit airplane. Auxiliary control flaps were tested in combinations with each wing. Data showing comparison of high-speed aerodynamic characteristics of the model when equipped with each wing, the effect of the auxiliary control flaps on aerodynamic characteristics, and elevator effectiveness for the model with the 66-series wing are presented. High-speed aerodynamic characteristics of the model were improved with the 66-series wing.
    Keywords: Aerodynamics
    Type: NACA-WR-A-90
    Format: application/pdf
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  • 14
    Publication Date: 2019-06-28
    Description: Correlation is established between aerodynamic characteristics of control surfaces in two-dimensional and three-dimensional flow. Slope of lift curve was affected little by overhang and balance-nose shape, but increased by sealing flap-nose gap. Effectiveness of balancing tab was same for sealed plain flap and unsealed overhang flap. Changes in hinge-moment coefficient were diminished by sealing gap. Values measured by three-dimensional flow disagreed with two-dimensional flow values until aspect ratio corrections were made.
    Keywords: Aerodynamics
    Type: NACA-WR-L-186 , NACA-ARR-L4I11F
    Format: application/pdf
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  • 15
    Publication Date: 2019-06-28
    Description: An investigation was made in the LMAL 7- by 10-foot wind tunnel of a NACA 23021 airfoil with a double slotted flap having a chord 32 percent of the airfoil chord (0.32c) to determine the aerodynamic section characteristics with the flaps deflected at various positions. The effects of moving the fore flap and rear flap as a unit and of deflecting or removing the lower lip of the slot were also determined. Three positions were selected for the fore flap and at each position the maximum lift of the airfoil was obtained with the rear flap at the maximum deflection used at that fore-flap position. The section lift of the airfoil increased as the fore flap was extended and maximum lift was obtained with the fore flap deflected 30 deg in the most extended position. This arrangement provided a maximum section lift coefficient of 3.31, which was higher than the value obtained with either a 0.2566c or a 0.40c single-slotted-flap arrangement and 0.25 less than the value obtained with a 0.4c double-slotted-flap arrangement on the same airfoil. The values of the profile-drag coefficient obtained with the 0.32c double slotted flap were larger than those for the 0.2566c or 0.40c single slotted flaps for section lift coefficients between 1.0 and approximately 2.7. At all values of the section lift coefficient above 1.0, the 0.40c double slotted flap had a lower profile drag than the 0.32c double slotted flap. At various values of the maximum section lift coefficient produced by various flap defections, the 0.32c double slotted flap gave negative section pitching-moment coefficients that were higher than those of other slotted flaps on the same airfoil. The 0.32c double slotted flap gave approximately the same maximum section lift coefficient as, but higher profile-drag coefficients over the entire lift range than, a similar arrangement of a 0.30c double slotted flap on an NACA 23012 airfoil.
    Keywords: Aerodynamics
    Type: NACA-WR-L-7 , NACA-ARR-L4J05
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  • 16
    Publication Date: 2019-06-28
    Description: Results of subject tests indicate the difficulty of obtaining closely balanced rudder surfaces for most tail assemblies with shielded horns and maintaining a near zero rate-of-change of hinge-moment coefficient without an additional balancing device. A comparison is made between shielded and unshielded horn test results. Pressure distribution and tuft tests of flow over different shaped horns showed higher critical speed for medium-taper nosed horn. The trim tab nose shape had little effect on tab test results.
    Keywords: Aerodynamics
    Type: NACA-WR-L-516 , NACA-ACR-4C11
    Format: application/pdf
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  • 17
    Publication Date: 2019-06-28
    Description: Wind-tunnel tests, investigating low drag wing performance in small-scale tests, showed a large increase in minimum drag coefficient, and a decrease of maximum lift coefficient occurred with decreasing Reynolds Number above certain designated values. The lift-curve slope varied up to 6% between high and low turbulence levels. Low Reynolds Number test data are unreliable for low drag airfoils either to estimate full-scale characteristics or to determine merits of airfoils for higher Reynolds numbers.
    Keywords: Aerodynamics
    Type: NACA-WR-L-138 , NACA-ACR-L4H11
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  • 18
    Publication Date: 2019-06-28
    Description: Tests were conducted at dynamic pressure of 50 lb per square foot with lift drag and pitch moment measurements throughout useful angle of attack range for constant flap deflection and position of a low-drag airfoil. Two slots were investigated and practical flap paths were selected for each Slot shape had a negligible effect on the maximum lift coefficient flap deflected, the rounded-entry slot had lower profile drag.
    Keywords: Aerodynamics
    Type: NACA-WR-A-80 , NACA-MR-A4L28
    Format: application/pdf
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  • 19
    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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  • 20
    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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  • 21
    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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  • 22
    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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  • 23
    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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