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  • 1
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    Validation of CFD for aircraft design: A Boeing view (1987)
    In:  CASI
    Details
    Publication Date: 2006-06-13
    Description: Information is given in viewgraph form on computational fluid dynamics (CFD) for aircraft design. Topics covered include CFD validation for advanced systems, cavity flow, transonic flow, separated flow, boundary layer interaction, hypersonic flow, heat transfer, zonal modeling, the mathematical foundation for Navier-Stokes simulation, hypersonic inlets, and the role of wind tunnel tests.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA. Ames Research Center, NASA CFD Validation Workshop; p 462-496
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    A progress report on the development of an augmentor wing jet STOL research aircraft. (1971)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The development of the aircraft has progressed to the point where the design of the modifications to the de Havilland C-8A Buffalo is complete and the engines are being tested. The predicted performance shows that the aircraft will be able to take off and land in less than 1500 ft. Simulation studies indicate that the handling qualities of the aircraft, with stability augmentation, will be acceptable for STOL research missions. Special techniques were required, however, for flight path control and transition from cruise to landing configuration .
    Keywords: AIRCRAFT
    Type: SAE PAPER 710757 , Society of Automotive Engineers, National Aeronautic and Space Engineering and Manufacturing Meeting; Sept. 28-30, 1971; Los Angeles, CA
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    Upper-surface blowing nacelle design study for a swept wing airplane at cruise conditions (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study was made to design two types of overwing nacelles for an existing wing-body at a design condition of Mach = 0.8 and C sub L = 0.2. Internal and external surface contours were developed for nacelles having either a D-shaped nozzle or a high-aspect-ratio nozzle for upper-surface blowing in the powered-lift mode of operation. The goal of the design was the development of external nacelle lines that would minimize high-speed aerodynamic interference effects. Each nacelle type was designed for both two- and four-engine airplanes using an iterative process of aerodynamic potential flow analysis. Incremental nacelle drag estimates were made for flow-through wind tunnel models of each configuration.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-2427 , D6-41763
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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