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  • AERODYNAMICS  (62)
  • ASTROPHYSICS  (41)
  • 1970-1974  (103)
  • 1940-1944
  • 1974  (103)
  • 1
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    Aerodynamic drag reduction tests on a full-scale tractor-trailer combination with several add-on devices (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Aerodynamic drag tests were performed on a conventional cab-over-engine tractor with a 45-foot trailer and five commercially available or potentially available add-on devices using the coast-down method. The tests ranged in velocity from approximately 30 miles per hour to 65 miles per hour and included some flow visualization. A smooth, level runway at Edwards Air Force Base was used for the tests, and deceleration measurements were taken with both accelerometers and stopwatches. An evaluation of the drag reduction results obtained with each of the five add-on devices is presented.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-56028 , Reduction of Aerodynamic Drag of Trucks Conf.; Oct 10, 1974 - Oct 11, 1974; Pasadena, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    An investigation of the cosmic radiation in the vicinity of the moon on the Luna 10, 11, and 12 artificial lunar satellites (1974)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Research on the primary cosmic radiation and solar cosmic rays from the Luna 10, 11, and 12 artificial lunar satellites is reviewed. Data on the vertical distribution of cosmic rays above the moon's surface are presented, and the albedo for the primary radiation is determined. The fluxes of electrons with energies from 30 to 300 keV were registered in the solar cosmic rays. Rapid variations of the electron flux were observed. The angular distributions of 0.5-10 MeV protons moving together with the corpuscular streams responsible for Forbush decreases were investigated.
    Keywords: ASTROPHYSICS
    Type: Interplanet. Medium and Phys. of the Magnetosphere (NASA-TT-F-784); p 151-173
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Axial flow measurements in trailing vortices (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A scanning laser Doppler velocimeter was used to measure the axial velocity defect in the cores of trailing vortices behind a lifting airfoil of rectangular planform. Data were obtained at several different angles of attack and downstream distances ranging from 30 to 1000 chord lengths. The test was designed to obtain continuous data from the near field into the far field while removing uncertainties associated with the interpretation of data obtained by the hydrogen bubble technique. The measured velocities of V sub x/U sub infinity are compared with those predicted. The agreement is remarkably good over the entire range of downstream distances, which supports the credibility of calculating axial velocities using the results of Moore and Saffman (1973).
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 12; Aug. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Vortex measurements behind a swept wing transport model (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A backscatter laser Doppler velocimeter which simultaneously senses the axial and the tangential components of the velocity has been used to measure the velocity distributions in the near wake of a swept wing semispan transport model in a wind tunnel. The model configuration included nacelles, pylons, antishock bodies, and wing flaps which could be deflected 27 deg. Typical wake vortex velocity profiles are presented for the flaps-retracted and the flaps-deployed 27 deg configurations, respectively.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 11; June 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Estimates of the Venus atmosphere optical characteristics with application to the problem of photographing its clouds and surface (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Optical parameters investigated and solved for included: (1) cloud layer albedo and cloud cover optical thickness; (2) planetary surface self-radiation influence; (3) light flux distribution as function of atmospheric height; (4) upper estimate of the observed contrasts; (5) surface optical parameters; and (6) contrast decrease with altitude.
    Keywords: ASTROPHYSICS
    Type: Space Iconics (NASA-TT-F-798); p 121-135
    Format: text
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  • 6
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    Applicability of the diffusion approximation (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Several methods using an approximate form of the scattering indicatrix are discussed for simplifying the calculation of radiation transport in planetary atmospheres.
    Keywords: ASTROPHYSICS
    Type: Space Iconics (NASA-TT-F-798); p 75-84
    Format: text
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  • 7
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    Effect of screen-induced total-pressure distortion on axial-flow compressor stability (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was made to determine the effects of screen-induced total-pressure distortions on two J85-GE-13 turbojet engines. Results were compared to those from a previous program run with a third engine. All compressors were found to be sensitive to a critical angle of circumferential distortion equal to 60 deg., and they all adhered closely to the parallel compressor model. The sensitivity of compressor exit pressure to virtually any type of distortion pattern can be determined by defining stall lines for undistorted, hub radial distorted, and tip radial distorted inflows. The effect of multiple sectors of circumferential distortion is defined.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3017 , E-7792
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Prospects for reduced energy transports: A preliminary analysis (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The recent energy crisis and subsequent substantial increase in fuel prices have provided increased incentive to reduce the fuel consumption of civil transport aircraft. At the present time many changes in operational procedures have been introduced to decrease fuel consumption of the existing fleet. In the future, however, it may become desirable or even necessary to introduce new fuel-conservative aircraft designs. This paper reports the results of a preliminary study of new near-term fuel conservative aircraft. A parametric study was made to determine the effects of cruise Mach number and fuel cost on the optimum configuration characteristics and on economic performance. For each design, the wing geometry was optimized to give maximum return on investment at a particular fuel cost. Based on the results of the parametric study, a nominal reduced energy configuration was selected. Compared with existing transport designs, the reduced energy design has a higher aspect ratio wing with lower sweep, and cruises at a lower Mach number. It has about 30% less fuel consumption on a seat-mile basis.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-62383
    Format: application/pdf
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  • 9
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    Conduct overall test operations and evaluate two Doppler systems to detect, track and measure velocities in aircraft wake vortices (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A program plan for system evaluation of the two-dimensional Scanning Laser Doppler System (SLDS) is presented. In order to meet system evaluation and optimization objectives the following tests were conducted: (1) noise tests; (2) wind tests; (3) blower flowfield tests; (4) single unit (1-D) flyby tests; and (5) dual unit (2-D) flyby tests. Test results are reported. The final phase of the program included logistics preparation, equipment interface checkouts, and data processing. It is concluded that the SLDS is capable of accurately tracking aircraft wake vortices from small or large aircraft, and in any type of weather.
    Keywords: AERODYNAMICS
    Type: NASA-CR-120600 , LMSC-HREC-TR-D390470
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Cold-air annular-cascade investigation of aerodynamic performance of cooled turbine vanes. 1: Facility description and base (solid) vane performance (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The aerodynamic performance of a solid vane was experimentally determined in a full-annular cascade, where three-dimensional effects could be obtained. This vane was of the same size and profile as the cooled vanes to be subsequently tested. The vanes were tested over a pressure ratio range that corresponded to mean-radius ideal aftermixed critical velocity ratios of 0.71 to 0.89. Overall vane aftermixed efficiencies were obtained over this range of critical velocity ratios and compared with results from a four-vane annular-sector cascade. The variation in vane aftermixed conditions and vane aftermixed efficiency with radius were also obtained and compared with design values. Vane surface static-pressure distributions were measured and compared with theory and with the results obtained in the four-vane cascade.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3006 , E-7699
    Format: application/pdf
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