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  • Other Sources  (19)
  • 2010-2014  (1)
  • 1975-1979  (18)
  • 1
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    Technology transfer: Another opinion (1975)
    In:  CASI
    Details
    Publication Date: 2005-02-28
    Keywords: URBAN TECHNOLOGY AND TRANSPORTATION
    Type: Calif. Univ. Res. in the Space Sci., Vol. 2, No. 1; 7 p
    Format: text
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  • 2
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    Measurement of the ozone profile in support of STRATCOM (1978)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: A rocket carrying an optical ozonesonde was launched at 1822 GMT on Sept. 29, 1977 in support of the STRATCOM 8 balloon. The integral ozone amount above the balloon ceiling altitude of 40 km was measured as .0117 atm-cm with an uncertainty less than + or - 7%. The ozone density at 40 km was 6.77 x 10 to the 17th power mol/cu m. Ozone densities in molecules/cu m at higher altitudes were 2.28 x 10 to the 17th power at 45 km, 6.72 x 10 to the 16th power at 50 km, 2.20 x 10 to the 16th power at 55 km, and 7.26 x 10 to the 15th power at 60 km. In addition, the ozone distribution was measured at lower altitudes from the tropopause at 17 km to 40 km.
    Keywords: GEOPHYSICS
    Type: STRATCOM 8 Data Workshop and Suppl.; p 49-55
    Format: text
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  • 3
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    Single-stage experimental evaluation of low aspect ratio, highly loaded blading for compressors. Part 9: Stage F and stage G, volume 1 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Two single-stage, 0.77 hub/tip ratio axial-flow compressors were tested to evaluate the effectiveness of low aspect ratio blading as a means of obtaining higher stage loadings. One compressor, designated Stage F, was comprised of circular arc blading with an aspect ratio of 0.9 for both the rotor and stator. This compressor was tested with uniform inlet flow, hub radial, tip radial, and 180 deg arc circumferential inlet distortion. The second compressor, designated Stage G, was comprised of multiple circular arc blading with an aspect ratio of 1.0 for both the rotor and stator. This compressor was tested with uniform inlet flow only. Design rotor tip speeds for Rotor F and Rotor G were 285 m/sec (934 ft/sec) and 327 m/sec (1,074 ft/sec) respectively. Both stages operated at high loading levels with adequate efficiency and operating range. The peak efficiencies and corresponding average stage diffusion factors for Stages F and G at design rotor speed were 86.4% and 84.1% and 0.59 and 0.55 respectively. The surge margin at peak efficiency for Stage F was 12.6% and the corresponding value for Stage G was 16.5%. Both stages experienced a loss in efficiency with increasing rotor speed; however, the multiple circular arc rotor delayed the characteristic loss in efficiency within increasing Mach number to higher Mach number.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134993 , PWA-FR-7033-PT-9-VOL-1
    Format: application/pdf
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  • 4
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    Single-stage experimental evaluation of low aspect ratio, highly loaded blading for compressors. Part 9: Stage F and stage G. Volume 2: Data supplement (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N76-23261.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134994 , PWA-FR-7033-PT-9-VOL-2
    Format: application/pdf
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  • 5
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    Soda ash removes sulfur from fuels (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Test show that adding soda ash (sodium bicarbonate) to coal/oil/water emulsion reduces 75 to 80% of sulfur dioxide gas emitted during subsequent combustion of emulsion.
    Keywords: MATERIALS
    Type: GSC-12403 , NASA Tech Briefs (ISSN 0145-319X); 4; 1; P. 69
    Format: text
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  • 6
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    30/20 GHz wideband technology verification program (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper discusses various aspects of the 30/20 GHz wideband technology verification activities of NASA. The discussion considers the objectives, approach, system requirements, possible experiment configuration and payload, and the supporting research and technology elements.
    Keywords: COMMUNICATIONS AND RADAR
    Type: In: ICC ''79; International Conference on Communications; Jun 10, 1979 - Jun 14, 1979; Boston, MA
    Format: text
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  • 7
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    Rocket ozone sounding network data (1979)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: During the period March 1977 through May 1977, three regular monthly ozone profiles were measured at Wallops Flight Center and three regular monthly ozone profiles were measured at the Churchill Research Range. One additional flight was conducted at Wallops Flight Center in support of Nimbus 4 SBUV. Data results and flight profiles for the period covered are presented.
    Keywords: GEOPHYSICS
    Type: NASA-TM-73283
    Format: application/pdf
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  • 8
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    Rocket ozone sounding network data (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: During the period December 1976 through February 1977, three regular monthly ozone profiles were measured at Wallops Flight Center, two special soundings were taken at Antigua, West Indies, and at the Churchill Research Range, monthly activities were initiated to establish stratospheric ozone climatology. This report presents the data results and flight profiles for the period covered.
    Keywords: GEOPHYSICS
    Type: NASA-TM-69365
    Format: application/pdf
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  • 9
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    Communication satellite services for special purpose users (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The present study identifies potential satellite services, examines the technology necessary for efficient implementation of these services, and determines minimum service cost versus user network size. The generic satellite services evaluated comprise TV and radio distribution (for retransmission), video teleconferencing (interactive), audio/facsimile teleconferencing (interactive), multiplexed data/voice (point-to-point), and satellite-supported land mobile. Satellite costs are based on extrapolations from ongoing commercial satellite programs. Production methods, new technology, and effect of production quantities on present and future production costs are examined to provide information on earth station equipment cost versus the variable 'buy'. Six different launch vehicles from a Delta 2914 to a dedicated Shuttle and three frequency bands and both broadcast (no eclipse capability) and fixed service satellites are considered to assess the effect of satellite size on cost and performance. It is assumed that the user pays only for his prorata share of the space segment costs.
    Keywords: COMMUNICATIONS AND RADAR
    Type: Intelcom ''77 Symposium; Oct 09, 1977 - Oct 15, 1977; Atlanta, GA
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  • 10
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    Hydrogen turbine power conversion system assessment (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A three part technical study was conducted whereby parametric technical and economic feasibility data were developed on several power conversion systems suitable for the generation of central station electric power through the combustion of hydrogen and the use of the resulting heat energy in turbogenerator equipment. The study assessed potential applications of hydrogen-fueled power conversion systems and identified the three most promising candidates: (1) Ericsson Cycle, (2) gas turbine, and (3) direct steam injection system for fossil fuel as well as nuclear powerplants. A technical and economic evaluation was performed on the three systems from which the direct injection system (fossil fuel only) was selected for a preliminary conceptual design of an integrated hydrogen-fired power conversion system.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-135298 , RI/RD77-252
    Format: application/pdf
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