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  • ASTROPHYSICS  (62)
  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE  (42)
  • 550 - Earth sciences
  • Life and Medical Sciences
  • MATERIALS, METALLIC
  • SPACE SCIENCES
  • 2010-2014
  • 1975-1979  (132)
  • 1970-1974
  • 1965-1969
  • 1950-1954  (14)
  • 1925-1929
  • 1975  (132)
  • 1954  (14)
Collection
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  • 2010-2014
  • 1975-1979  (132)
  • 1970-1974
  • 1965-1969
  • 1950-1954  (14)
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Year
  • 1
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    Full-scale upper-surface-blown flap noise (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A highly noise-suppressed TF 34 engine was used to investigate the noise of several powered lift configurations involving upper-surface-blown (USB) flaps. The configuration variables were nozzle type (i.e. slot and circular with deflector), flap chord-length, and flap angle. The results of velocity surveys at both the nozzle exit and the flap trailing edge are used for correlation of the noise data. Configurations using a long flap design were 4 dB quieter than a short flap typical of current trends in USB flap design. The lower noise for the long flap is attributed primarily to the greater velocity decay of the jet at the flap trailing edge. The full-scale data revealed substantially more quadrupole noise in the region near the deflected jet than observed in previous sub-scale tests.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 750609 , Society of Automotive Engineers, Air Transportation Meeting; May 06, 1975 - May 08, 1975; Hartford, CT
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Flight test investigation of the vortex wake characteristics behind a Boeing 727 during two-segment and normal ILS approaches (A joint NASA/FAA report) (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Flight tests were performed to evaluate the vortex wake characteristics of a Boeing 727 aircraft during conventional and two-segment instrument landing approaches. Smoke generators were used for vortex marking. The vortex was intentionally intercepted by a Lear Jet and a Piper Comanche aircraft. The vortex location during landing approach was measured using a system of phototheodolites. The tests showed that at a given separation distance there are no readily apparent differences in the upsets resulting from deliberate vortex encounters during the two types of approaches. The effect of the aircraft configuration on the extent and severity of the vortices is discussed.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-X-62398 , FAA-NA-75-151
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
    Electronic Resource
    Electronic Resource
    Centrifugal elutriation: Separation of spermatogenic cells on the basis of sedimentation velocity (1975)
    New York, NY [u.a.] : Wiley-Blackwell
    Journal of Cellular Physiology 86 (1975), S. 177-189 
    Details
    ISSN: 0021-9541
    Keywords: Life and Medical Sciences ; Cell & Developmental Biology
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Biology , Medicine
    Notes: Various types of cells from the testes of mice and hamsters were separated according to differences in sedimentation velocity by centrifugal elutriation, a counterflow centrifugation technique. Approximately 3 × 108 cells, prepared from six mouse testes or from one hamster testis, were separated into 11 fractions in less than two hours as compared to the 4-5 hours required for sedimentation at unit gravity (“Staput”). Fractions enriched in elongated spermatids and spermatozoa (100%), stages 1-8 spermatids (69%) and pachytene spermatocytes (58%) were obtained from mouse testis dispersions. Similarly enriched fractions were obtained from hamster cells. A single fraction enriched in stages 1-8 spermatids (mouse) was prepared in less than 30 minutes. As many as 2 × 109 cells were separated in a single procedure. Spermatogenic cells exhibited no evidence of structural damage with trypan blue and phase microscopy, and recovery was essentially 100%. Centrifugal elutriation had no effect on sperm motility or on the plating efficiency of CHO cells.
    Additional Material: 4 Tab.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/jcp.1040860119
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    Paper (German National Licenses)
    Fulltext
  • 4
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    Gravitational theories with nonzero divergence of the energy-momentum tensor (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Assuming that the divergence of the energy-momentum tensor is nonzero leads to a class of theories with consistent field equations and gauge conditions as well as compatibility with the Newtonian limit of the conservation laws. Both the Einstein and the Brans-Dicke theories are used as models, but the extension to other viable theories such as vector-metric and two-metric theories is possible. One particularly interesting theory emerges that agrees with the ordinary Brans-Dicke theory except for the post-Newtonian parameter zeta sub 2, which predicts nonconservation of total momentum. Unfortunately, no accurate experimental limits for this parameter are known. It thus remains for future experiments in lunar-laser ranging to test this theory.
    Keywords: ASTROPHYSICS
    Type: Physical Review D - Particles and Fields; vol. 12
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Radio detection of interstellar sulfur dioxide (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Interstellar sulfur dioxide (SO2) has been detected in emission from the direction of the Orion Nebula molecular cloud and from Sgr B2. SO2 is the heaviest interstellar molecule detected to date, and the only nonlinear triatomic molecule which does not contain hydrogen. The remarkable Orion emission profiles suggest that two components are supporting the SO2 emission: a dense circumstellar-type envelope, which may be in maser emission, and a warm galactic cloud component.
    Keywords: ASTROPHYSICS
    Type: Astrophysical Journal; 198; June 1
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    The infrared excess of cool giant stars - A chromospheric contribution (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The idea that the infrared excesses of evolved M stars may contain a contribution from a chromosphere is explored using alpha Ori and W Hya as test cases. The spectrum of alpha Ori between 8 and 30 millimicrons can be interpreted satisfactorily in terms of three components: a photosphere, a silicate dust cloud, and a cool chromosphere (temperature about 5000 K), which is optically thick at 14 millimicrons. A similar modelling for W Hya suggests a hotter chromosphere (temperature about 8000 K), with unit optical depth at 30 millimicrons. Some consequences of these chromospheres are briefly discussed.
    Keywords: ASTROPHYSICS
    Type: Royal Astronomical Society; vol. 172
    Format: text
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  • 7
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    Relativistic astrophysics (1975)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The coordinate independence of gravitational radiation and the parameterized post-Newtonian approximation from which it is extended are described. The general consistency of the field equations with Bianchi identities, gauge conditions, and the Newtonian limit of the perfect fluid equations of hydrodynamics are studied. A technique of modification is indicated for application to vector-metric or double metric theories, as well as to scalar-tensor theories.
    Keywords: ASTROPHYSICS
    Type: NASA-CR-142988 , FR-4
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Conceptual design of reduced energy transports (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper reports the results of a conceptual design 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. Supercritical wing technology and advanced engine cycles were assumed. 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 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 yields about 30% more seat-miles/gal than current wide-body aircraft. At the higher fuel costs anticipated in the future, the reduced energy design has about the same economic performance as existing designs.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 75-303 , American Institute of Aeronautics and Astronautics, Annual Meeting and Technical Display; Feb 24, 1975 - Feb 26, 1975; Washington, DC
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Display/control requirements for VTOL aircraft (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Quantative metrics were determined for system control performance, workload for control, monitoring performance, and workload for monitoring. Pilot tasks were allocated for navigation and guidance of automated commercial V/STOL aircraft in all weather conditions using an optimal control model of the human operator to determine display elements and design.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-145026 , ASI-TR-75-26
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Simultaneous calculation of aircraft design loads and structural member sizes (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A design process which accounts for the interaction between aerodynamic loads and changes in member sizes during sizing of aircraft structures is described. A simultaneous iteration procedure is used wherein both design loads and member sizes are updated during each cycle yielding converged, compatible loads and member sizes. A description is also given of a system of programs which incorporates this process using lifting surface theory to calculate aerodynamic pressure distributions, using a finite-element method for structural analysis, and using a fully stressed design technique to size structural members. This system is tailored to perform the entire process with computational efficiency in a single computer run so that it can be used effectively during preliminary design. Selected results, considering maneuver, taxi, and fatigue design conditions, are presented to illustrate convergence characteristics of this iterative procedure.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 75-965 , American Institute of Aeronautics and Astronautics, Aircraft Systems and Technology Meeting; Aug 04, 1975 - Aug 07, 1975; Los Angeles, CA
    Format: text
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