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  • AERODYNAMICS  (950)
  • 2020-2024
  • 2010-2014
  • 1980-1984  (594)
  • 1970-1974  (354)
  • 1945-1949  (2)
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  • 1
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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
  • 2
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    User's manual for the coupled mode version of the normal modes rotor aeroelastic analysis computer program (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This User's Manual was prepared to provide the engineer with the information required to run the coupled mode version of the Normal Modes Rotor Aeroelastic Analysis Computer Program. The manual provides a full set of instructions for running the program, including calculation of blade modes, calculations of variable induced velocity distribution and the calculation of the time history of the response for either a single blade or a complete rotor with an airframe (the latter with constant inflow).
    Keywords: AERODYNAMICS
    Type: NASA-CR-137899 , SER-50910
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    An experimental study of airfoil icing characteristics (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The present investigation is concerned with the icing characteristics of a general aviation wing section, taking into account selected results from icing wind tunnel tests of the wing section. Drag coefficient increases of about 130 percent were measured for a 20 minute glaze icing encounter and cruise aerodynamic conditions. The drag increased by about 40 percent for a 15 minute rime icing encounter and the same aerodynamic conditions. The considered wing section was found to be less sensitive to rime and glaze ice accretions occurring for the climb aerodynamic conditions. The observed aft frost layer growths contributed significantly to the measured increase in section drag coefficient level. Comparisons of measured increases in section drag coefficient due to the primary ice accretion with predictions of NACA drag correlation indicated agreement was as good as that for the original data upon which the correlation was based.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 82-0283 , Aerospace Sciences Meeting; Jan 11, 1982 - Jan 14, 1982; Orlando, FL
    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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    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
  • 6
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    The role of freestream turbulence scale in subsonic flow separation (1984)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The ojective of this work is the clarification of the role of freestream turbulence scale in determining the location of boundary layer separation. An airfoil in subsonic wind tunnel flow is the specific case studied. Hot-film and hot-wire anemometry, liquid-film visualization and pressure measurements are the principal diagnostic techniques in use. The Vanderbilt University subsonic wind tunnel is the flow facility being used.
    Keywords: AERODYNAMICS
    Type: NASA-CR-174172 , NAS 1.26:174172 , IPR-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    The use of oil for in-flight flow visualization (1984)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Oil was used to visualize inflight aerodynamic characteristics such as boundary layer transition, shock wave location, regions of separated flow, and surface flow direction. The technique, which is similar to wind tunnel oil-flow testing, involves an oil mixture to test aircraft before takeoff. After takeoff, the airplane climbs immediately to the test altitude and photographs are taken. The developmental experience is summarized, several examples of inflight oil-flow photographs are presented and discussed, and an approach for potential users of the technique is presented.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84915 , H-1195 , NAS 1.15:84915 , Ann. Symp. of the Soc. of Flight Test Engr.; Aug 15, 1983 - Aug 19, 1983; Newport Beach, Ca; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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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
  • 9
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    Flyover and static tests to investigate external flow effect on jet noise for nonsuppressor and suppressor exhaust nozzles. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 73-190 , Aerospace Sciences Meeting; Jan 10, 1973 - Jan 12, 1973; Washington, DC
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Flutter of pairs of aerodynamically interfering delta wings. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: To examine the effect on flutter of the aerodynamic interference between pairs of closely spaced delta wings, several structurally uncoupled 1/80th-scale models were studied by experiment and analysis. Flutter test boundaries obtained in NASA Langley's 26-in. transonic blowdown wind tunnel were compared with subsonic analytical results generated using the doublet lattice method. Trends for several combinations of vertical and longitudinal wing separation were determined, showing flutter speed significantly affected in the closely spaced configurations. A new flutter mechanism coupling one wing's first bending mode with the other wing's first torsion mode was predicted and observed.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 73-314 , Dynamics Specialists Conference; Mar 19, 1973 - Mar 20, 1973; Williamsburg, VA
    Format: text
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    NASA TECHNICAL REPORTS
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