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  • LUNAR AND PLANETARY EXPLORATION  (1,311)
  • AERODYNAMICS  (785)
  • SPACE SCIENCES
  • 1980-1984  (2,096)
  • 1955-1959
  • 1982  (1,129)
  • 1981  (967)
  • 1973
  • 1970
Collection
Keywords
Years
Year
  • 1
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    Voyages to Saturn (1982)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The Voyager mission to Saturn is explained in detail. A history of Saturn observations from ancient times to the present is given. The Voyager spacecraft and their instruments are described. An overview of planetary astronomy is presented. The text is supplemented by numerous black and white and color photographs. The Saturn satellites are discussed in detail, and preliminary pictorial maps of the satellites are given.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: NASA-SP-451 , NAS 1.21:451 , LC-81-600073
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Multidomain approach for calculating compressible flows (1982)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A multidomain approach for calculating compressible flows by using unsteady or pseudo-unsteady methods is presented. This approach is based on a general technique of connecting together two domains in which hyperbolic systems (that may differ) are solved with the aid of compatibility relations associated with these systems. Some examples of this approach's application to calculating transonic flows in ideal fluids are shown, particularly the adjustment of shock waves. The approach is then applied to treating a shock/boundary layer interaction problem in a transonic channel.
    Keywords: AERODYNAMICS
    Type: NASA-TM-76692 , NAS 1.15:76692
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Current developments lighter than air systems (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Lighter than air aircraft (LTA) developments and research in the United States and other countries are reviewed. The emphasis in the U.S. is on VTOL airships capable of heavy lift, and on long endurance types for coastal maritime patrol. Design concepts include hybrids which combine heavier than air and LTA components and characteristics. Research programs are concentrated on aerodynamics, flight dynamics, and control of hybrid types.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84744 , NAS 1.15:84744
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    The Viking seismometry (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Efforts were made to determine the seismicity of Mars as well as define its internal structure by detecting vibrations generated by marsquakes and meteoroid impacts. The lack of marsquakes recognized in the Viking data made it impossible to make any direct inferences about the interior of Mars and only allowed the setting of upper bounds on the seismic activity of the planet. After obtaining more than 2100 hours worth of data during the quite periods at rates of one sample per second or higher, the Viking 2 seismometer was turned off as a consequence of a landing system failure. During the periods when adequate data were obtained, one event of possible seismic or meteoroid impact origin was recognized; however, there is a significant probability that this event was generated by a wind gust.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: NASA-CR-3408
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Experimental investigation of the flow on the suction side of a thin Delta wing (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Surface oil flow patterns were photographed and pressure distribution measurements were carried out on a sharp edged delta wing of aspect ratio lambda = 1.0 in order to determine the influence of Reynolds number and of vortex breakdown on the flow on the suction side of the wing. The formation of the secondary vortex occurs due to separation of a laminar boundary layer in the front part of the wing and due to separation of a turbulent boundary layer in the rear part of the wing. In the case of turbulent separation, the secondary separation line is closer to the wing leading edge than in the laminar case. The position of the transition depends on the Reynolds number and on the angle of incidence. The breakdown of a vortex above the wing leads to a kink in the secondary separation line.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75897
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Aerodynamics on a transport aircraft type wing-body model (1982)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The DFLR-F4 wing-body combination is studied. The 1/38 model is formed by a 9.5 aspect ratio transonic wing and an Airbus A 310 fuselage. The F4 wing geometrical characteristics are described and the main experimental results obtained in the S2MA wind tunnel are discussed. Both wing-fuselage interferences and viscous effects, which are important on the wing due to a high rear loading, are investigated by performing 3D calculations. An attempt is made to find their limitations.
    Keywords: AERODYNAMICS
    Type: NASA-TM-76878 , NAS 1.15:76878
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Thermal inertia mapping of Mars from 60 deg S to 60 deg N (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: The considered region comprises 81% of the surface of Mars. Thermal inertia I is a composite surface property, which is equal to the square root of the product of three factors, including the thermal conductivity, the density, and the specific heat. I is the sole thermal parameter which governs the temperature variation of a periodically heated homogeneous surface, and, as such, is the prime intermediary between remote temperature observations and their geologic interpretation. The values for the thermal inertia found imply particulate surface materials. The variation in Martian surface thermal conductivity is about two orders of magnitude. Three large regions of low-inertia material are defined. Low-inertia material always possesses high albedo. There is a general tendency for higher-thermal-inertia surfaces to be darker but exceptions occur which may be related to a thin mantling of light dust or bonding of light material.
    Keywords: LUNAR AND PLANETARY EXPLORATION
    Type: Icarus; 45; Feb. 198
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Separation behavior of boundary layers on three-dimensional wings (1981)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: An inverse boundary layer procedure for calculating separated, turbulent boundary layers at infinitely long, crabbing wing was developed. The procedure was developed for calculating three dimensional, incompressible turbulent boundary layers was expanded to adiabatic, compressible flows. Example calculations with transsonic wings were made including viscose effects. In this case an approximated calculation method described for areas of separated, turbulent boundary layers, permitting calculation of this displacement thickness. The laminar boundary layer development was calculated with inclined ellipsoids.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75877
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    A study of dirigibles for use in the Peruvian Selva Central region (1982)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The potential for dirigibles as transports in the Selva Central region of Peru was evaluated by means of a mission and economic analysis. A total requirement to transport over 19 million tons (t) of agricultural produce, lumber and meat was projected by the year 2004. A primary route involving zones for loading and delivering this carbo was identified. Although dirigibles are capable of short field operation, all existing airfields must be enlarged in width to allow for all conditions of wind and weather and to provide space for overnight mooring. A maintenance base and operations headquarters, complete with hangar and other service facilities would be required. The quantities of cargo capacities of 5 to 100 tons were identified. Fleet sizes up to 106 dirigibles (in 20 t capacities) would be required. Dirigibles were assumed to be of the nonrigid type except in the 100 t category for which rigid characteristics were assumed. A method of determining dirigible costs was developed. The values derived were then applied to an economic analysis to determine initial investment and operating costs. It was found that larger dirigibles of approximately 20 t capacities or higher could offer significant cost benefits over airplanes, provided cruise speeds were higher than 100km/hr.
    Keywords: AERODYNAMICS
    Type: NASA-TM-85634 , NAS 1.15:85634
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    The calculation of separated flow at helicopter bodies (1982)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: For abstract see A81-47555.
    Keywords: AERODYNAMICS
    Type: NASA-TM-76715 , NAS 1.15:76715
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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