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  • 1
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    Computational support of the X-29A Advanced Technology Demonstrator flight experiment (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Issues and questions associated with the forward swept wing and closely coupled canard are addressed. The primary focus will be on research questions which must be addressed to obtain high quality ground and flight test data. These data will be used in conjunction with computational predictions to complement the analyses required to comprehensively understand the interacting technologies.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Transonic Symposium: Theory, Application and Experiment, Volume 2; p 147-166
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    X-29 Flight Test Program including wind tunnel and computational support (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A cooperative effort has been defined between NASA-Ames/Dryden Flight Research Facility and NASA-Langley Research Center in support of the X-29A Advanced Technology Demonstrator. The effort involves three phases: flight testing, wind-tunnel testing in the National Transonic Facility, and computational support of each experimental phase. These efforts are primarily aimed at understanding the complex flow phenomena and component interactions associated with the X-29A. Each phase of the effort is discussed in detail and initial data comparisons are presented. In summary, the synergistics effects of the complementary phases are identified, which will enhance the understanding of the unique aerodynamics of the X-29A.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 861642
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Space Shuttle third flight /STS-3/ entry RCS analysis (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Flight data obtained from three Space Transportation System orbiter entries (STS-1, 2, and 3) are processed and analyzed to determine the roll interactions caused by the firing of the entry reaction control system (RCS). Comparisons between the flight-derived parameters and the predicted derivatives without interaction effects are made. The flight-derived RCS Plume flow-field interaction effects are independently deduced by direct integration of the incremental changes in the wing upper surface pressures induced by RCS side thruster firings. The separately obtained interaction effects are compared to the predicted values and the differences are discussed.
    Keywords: SPACE TRANSPORTATION
    Type: AIAA PAPER 83-0116 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 10, 1983 - Jan 13, 1983; Reno, NV
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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