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  • Other Sources  (10)
  • Aircraft Design, Testing and Performance  (7)
  • Waves  (2)
  • 42.74
  • Earth model, also for more shallow analyses !
  • Inorganic Chemistry
  • LUNAR AND PLANETARY EXPLORATION
  • Organic Chemistry
  • Review article
  • 1935-1939  (10)
  • 1938  (10)
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  • 1935-1939  (10)
Year
  • 1
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    Seismic waves in the core of the earth (1938)
    In:  Nature, Milano, Gustav Fischer, vol. 141, no. 6, pp. 371, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1938
    Keywords: Waves ; Seismology ; earth Core
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    P' and the earth's core (1938)
    In:  Month. Notices Royal astr. Soc., Geophys. Suppl., Milano, Gustav Fischer, vol. 4, no. 6, pp. 363-372, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1938
    Keywords: Waves ; earth Core ; P-waves ; Diffraction
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    Determination of Venus winds by ground-based radio tracking of the VEGA balloons (1938)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A global array of 20 radio observatories was used to measure the three-dimensional position and velocity of the two meteorological balloons that were injected into the equatorial region of the Venus atmosphere near Venus midnight by the VEGA spacecraft on June 11 and 15, 1985. Initial analysis of only radial velocities indicates that each balloon was blown westward about 11,500 kilometers (8,000 kilometers on the night side) by zonal winds with a mean speed of about 70 meters per second. Excursions of the data from a model of constant zonal velocity were generally less than 3 meters per second; however, a much larger variation was evident near the end of the flight of the second balloon. Consistent systematic trends in the residuals for both balloons indicate the possibility of a solar-fixed atmospheric feature. Rapid variations in balloon velocity were often detected within a single transmission (330 seconds); however, they may represent not only atmospheric motions but also self-induced aerodynamic motions of the balloon.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Science (ISSN 0036-8075); 231; 1414-141
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Preliminary Fatigue Studies on Aluminum Alloy Aircraft Girders (1938)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Preliminary information on the complex subject of the fatigue strength of fabricated structural members for aircraft is presented in the test results obtained on several different types of airship girders subjected to axial tension and compression in a resonance fatigue machine. A description of this machine as well as numerous photographs of the fatigue failures are given. There is also presented an extended bibliography on the subject of fatigue strength.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TN-637
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Preliminary Full-Scale Wind-Tunnel Investigation of Wing Ducts for Radiators, Special Report (1938)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Wing ducts for liquid-cooled engine radiators have been investigated in the N.A.C.A. full-scale wind tunnel on a large model airplane. Th e tests were made to determine the relative merits of several types of duct and radiator installations for an airplane of a particular des ign. In the test program the principal duct dimensions were system atically varied, and the results are therefore somewhat applicable to the general problems of wing duct design, although they should be co nsidered as preliminary and only indicative of the inherent possibil ities.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-88
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Wind-Tunnel Investigation of Air Inlet and Outlet Openings for Aircraft, Special Report (1938)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation was made in the NACA 5-foot vertical wind tunnel of a large variety of duct inlets and outlets to obtain information relative to their design for the cooling or the ventilation systems on aircraft. Most of the tests were of openings in a flat plate but, in order to determine the best locations and the effects of interference, a few tests were made of openings in an airfoil. The best inlet location for a system not including a blower was found to be at the forward stagnation point; for one including a blower, the best location was found to be in the region of lowest total head, probably in the boundary layer near the trailing edge. Design recommendations are given, and it is shown that correct design demands a knowledge of the external flow and of the internal requirements in addition to that obtained from the results of the wind tunnel tests.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-95
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Full-Scale Wind-Tunnel Investigation of Wing Cooling Ducts, Special Report (1938)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The systematic investigation of wing cooling ducts at the NACA laboratory has been continued with tests in the full-scale wind tunnel on ducts of finite span. These results extend the previous investigation on section characteristics of ducts to higher Reynolds numbers and indicate the losses due to the duct ends. The data include comparisons between ducts completely within the ring and the conventional underslung ducts. Methods of flow regulation were studied and data were obtained for a wide range of internal duct resistance. The results show satisfactory correlation between the finite span and the previously measured section characteristics obtained with full-span ducts. The effects of the various design parameters on the duct characteristics are discussed. The cooling power required for the internal duct installation is shown to be only a small percentage of the engine power.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-94
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Investigation in the 7-By-10 Foot Wind Tunnel of Ducts for Cooling Radiators Within an Airplane Wing, Special Report (1938)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An investigation was made in the NACA 7- by 10-foot wind tunnel of a large-chord wing model with a duct to house a simulated radiator suitable for a liquid-cooled engine. The duct was expanded to reduce the radiator losses, and the installation of the duct and radiator was made entirely within the wing to reduce form and interference drag. The tests were made using a two-dimensional flow set-up with a full-span duct and radiator. Section aerodynamic characteristics of the basic airfoil are given and also curves showing the characteristics of the various duct-radiator combinations. An expression for efficiency, the primary criterion of merit of any duct, and the effect of the several design parameters of the duct-radiator arrangement are discussed. The problem of throttling is considered and a discussion of the power required for cooling is included. It was found that radiators could be mounted in the wing and efficiently pass enough air for cooling with duct outlets located at any point from 0.25c to 0.70c from the wing leading edge on the upper surface. The duct-inlet position was found to be critical and, for maximum efficiency, had to be at the stagnation point of the airfoil and to change with flight attitude. The flow could be efficiently throttled only by a simultaneous variation of duct inlet and outlet sizes and of inlet position. It was desirable to round both inlet and outlet lips. With certain arrangements of duct, the power required for cooling at high speed was a very low percentage of the engine power.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-93
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    The Torsional and Bending Deflection of Full-Scale Duralumin Propeller Blades under Normal Operating Conditions, Special Report (1938)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The torsional deflection of the blades of three full-scale duralumin propellers operating under various loading conditions was measured by a light-beam method. Angular bending deflections were also obtained as an incidental part of the study. The deflection measurements showed that the usual present-day type of propeller blades twisted but a negligible amount under ordinary flight conditions. A maximum deflection of about 1/10th of a degree was found at V/nD of 0.3 and a smaller deflection at higher values of V/nD for the station at 0.70 radius. These deflections are much smaller than would be expected from earlier tests, but the light-beam method is considered to be much more accurate than the direct-reading transit method used in the previous tests.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-84
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    N.A.C.A. Stall-Warning Device (1938)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: With some airplanes the approach to the stall is accompanied by changes in the behavior, such as tail buffeting or changes in the control characteristics of the airplane so that the pilot obtains a warning of the impending stall. Vith other airplanes it is possible to approach the stall without any perceptible warning other than the reading of the air-speed meter, in which case the danger of inadvertent stalling is considerably greater. Although it is not within the scope of this paper to discuss stalling characteristics, it is desired to point out that in general the danger of inadvertent stalling is greatest with those airplanes that behave worse when the stalling occurs; that is, with airplanes in which the stall starts at the wing tips. A warning of the impending stall is desirable in any case, but is particularly desirable with airplanes of the latter type.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-80
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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