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  • AERODYNAMICS  (4)
  • COMPOSITE MATERIALS  (2)
  • SPACECRAFT INSTRUMENTATION  (2)
  • 2020-2021
  • 1980-1984  (8)
  • 1950-1954
  • 1
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    Seasat-A satellite scatterometer instrument evaluation (1980)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The Seasat-A satellite scatterometer (SASS) was designed to measure ocean surface wind speed and direction in twenty-four independent cells over a 1000-km swath. It operated in the interrupted CW mode at a frequency of 14.6 GHz with four fan beam antennas and used Doppler filtering in the receiver for resolving the cells on the surface. The instrument began operating in space on July 6, 1978, and gathered normalized radar cross section data for approximately 2290 h. The purpose of this paper is to describe the in-orbit evaluation of the SASS hardware and its compatibility with the spacecraft. It has been determined that the scatterometer operated flawlessly throughout the mission, met all design requirements, and established a good data base for geophysical processing.
    Keywords: SPACECRAFT INSTRUMENTATION
    Type: IEEE Journal of Oceanic Engineering; OE-5; Apr. 198
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Zero-length inlets for subsonic V/STOL aircraft (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Previously cited in issue 19, p. 3257, Accession no. A81-42186
    Keywords: AERODYNAMICS
    Type: (ISSN 0021-8669)
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Validation of temperature retrievals obtained by the Limb Infrared Monitor of the Stratosphere (LIMS) experiment on Nimbus 7 (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An outline is given of LIMS temperature determinations (as a function of pressure) from measurements in two channels covering portions of the 15-micrometer band of carbon dioxide. The known sources of error from the radiometer and data reduction are used to estimate the systematic and random errors expected of the results. Observational determinations of the complete end-to-end precision are obtained by computing the standard deviation of six sequential temperature retrievals in regions where the atmosphere is horizontally uniform. This yields values of 0.2 to 0.6 K, in reasonable agreement with the estimates. A correction for horizontal gradients in the atmosphere leads to a large reduction in the differences between the stratospheric temperatures determined on the ascending and descending portions of the orbit. The temperatures agree in the mean with radiosondes and rocketsondes to within 1-2 K in most regions below 1 mbar. Several interesting, previously unseen features included cold regions in the mid-latitude mesosphere and wavelike vertical variations in the tropics.
    Keywords: SPACECRAFT INSTRUMENTATION
    Type: Journal of Geophysical Research (ISSN 0148-0227); 89; 5147-516
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Zero-length, slotted-lip inlet for subsonic military aircraft (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Zero-length, slotted-lip inlet performance and associated fan blade stresses were determined during model tests using a 20-inch diameter fan simulator in the NASA-LeRC 9- by 15-foot low-speed wind tunnel. The model configuration variables consisted of inlet contraction ratio, slot width, circumferential extent of slot fillers, and length of a constant area section between the inlet throat and fan face. Inlet configurations having contraction ratios of 1.2 and 1.3 satisfied all critical low-speed inlet operating requirements for a fixed horizontal nacelle and tilt-nacelle-type subsonic V/STOL aircraft, respectively. Relative to a conventional axisymmetric tilt-nacelle inlet, the zero-length, slotted-lip inlet has a 27-percent smaller inlet lip contraction ratio, an 83-percent shorter total length, and a 5-percent smaller maximum cowl diameter.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 80-1245 , Joint Propulsion Conference; Jun 30, 1980 - Jul 02, 1980; Hartford, CT
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    An investigation of adhesive/adherend and fiber/matrix interactions. Part B: SEM/ESCA analysis of fracture surfaces (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Adhesion was studied with emphasis on the characterization of surface oxide layers, the analysis of fracture surfaces, and the interaction of matrices and fibers. A number of surface features of the fractured lap shear samples were noted in the SEM photomicrographs including the beta phase alloy of the Ti 6-4 adherend, the imprint of the adherend on the adhesive failure surface, increased void density for high temperature samples, and the alumina filler particles. Interfacial failure of some of the fractured lap shear samples is invariably characterized by the appearance of an ESCA oxygen photopeak at 530.3 eV assigned to the surface oxide layer of Ti 6-4 adherend. The effect of grit blasting on carbon fiber composites is evident in the SEM analysis. A high surface fluorine concentration on the composite surface is reduced some ten fold by grit blasting.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-CR-169798 , NAS 1.26:169798
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Wind tunnel tests of a zero length, slotted-lip engine air inlet for a fixed nacelle V/STOL aircraft (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Zero length, slotted lip inlet performance and associated fan blade stresses were determined during model tests using a 20 inch diameter fan simulator in the NASA-LeRC 9 by 15 foot low speed wind tunnel. The model configuration variables consisted of inlet contraction ratio, slot width, circumferential extent of slot fillers, and length of a constant area section between the inlet throat and fan face. The inlet performance was dependent on slot gap width and relatively independent of inlet throat/fan face spacer length and slot flow blockage created by 90 degree slot fillers. Optimum performance was obtained at a slot gap width of 0.36 inch. The zero length, slotted lip inlet satisfied all critical low speed inlet operating requirements for fixed horizontal nacelles subsonic V/STOL aircraft.
    Keywords: AERODYNAMICS
    Type: NASA-TM-82939 , E-1338 , NAS 1.15:82939
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Zero-length inlets for subsonic V/STOL aircraft (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Zero-length inlet performance and associated fan blade stresses were determined during model tests in the NASA-LeRC 9-by 15-foot low-speed wind tunnel. The inlet models, which were installed on a 20-inch diameter fan unit, had different inlet lip contraction ratios as well as unslotted, slotted, and double slotted inlet lips. The inlet angle-of-attack boundaries for onset of flow separation were identified and compared to the operating requirements of several generically different subsonic V/STOL aircraft. The zero-length inlets, especially those with slotted lips, were able to satisfy these requirements without compromising the maximum cowl forebody radius. As an aid to the inlet design process, a unique relationship was established between the maximum surface Mach number associated with the separation boundary and the maximum-to-throat surface velocity ratio.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 81-1396 , Joint Propulsion Conference; Jul 27, 1981 - Jul 29, 1981; Colorado Springs, CO; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    An investigation of adhesive/adherend and fiber matrix interactions (1981)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Research during the report period focused on continued scanning electron microscopy (SEM) and X-ray photoelectron spectroscopy (XPS) of lap shear samples and flatwise tensile specimens and on the surface characterization of TiO2, Ti 6-4, and Ti powders with particular emphasis on their interaction with primer solutions of both polyphenylquinoxaline and LaRC-13 polyimide. The use of SEM and XPS in the analysis of Ti 6-4 adherend surfaces is described as well as differences in Ti 6-4 surface composition after different chemical pretreatments. Analysis of fractured surfaces is used to established the failure mode. The surface acidity of Ti 6-4 coupons can be established by reflectance visible spectroscopy using indicator dyes.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-CR-164836
    Format: application/pdf
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