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  • AIRCRAFT PROPULSION AND POWER  (3)
  • AIRCRAFT STABILITY AND CONTROL  (1)
  • 1
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    Two-dimensional viscous flow computations of hypersonic scramjet nozzle flowfields at design and off-design conditions (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The PARC2D code has been selected to analyze the flowfields of a representative hypersonic scramjet nozzle over a range of flight conditions from Mach 3 to 20. The flowfields, wall pressures, wall skin friction values, heat transfer values and overall nozzle performance are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 88-3280
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    Two-dimensional viscous flow computations of hypersonic scramjet nozzle flowfields at design and off-design conditions (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The PARC2D code has been selected to analyze the flowfields of a representative hypersonic scramjet nozzle over a range of flight conditions from Mach 3 to 20. The flowfields, wall pressures, wall skin friction values, heat transfer values and overall nozzle performance are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-182150 , E-4190 , NAS 1.26:182150
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 3
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    Comparison of 3D computation and experiment for non-axisymmetric nozzles (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Three-dimensional solutions of a single expansion ramp nozzle are computed with the existing PARC computer code by solving the full Navier-Stokes equations. The computations are performed to simulate the non-axisymmetric nozzle flowfield in both the internal/external expansion regions and the exhaust plume in a quiescent ambient environment. Two different configurations of the nozzle at a pressure ratio NPR = 10 are examined. Numerical results of laminar flows are presented, and the wall pressure distributions are compared with the experimental data.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 89-0007
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 4
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    Control methods for aiding a pilot during STOL engine failure transients (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Candidate autopilot control laws that control the engine failure transient sink rates by demonstrating the engineering application of modern state variable control theory were defined. The results of approximate modal analysis were compared to those derived from full state analyses provided from computer design solutions. The aircraft was described, and a state variable model of its longitudinal dynamic motion due to engine and control variations was defined. The classical fast and slow modes were assumed to be sufficiently different to define reduced order approximations of the aircraft motion amendable to hand analysis control definition methods. The original state equations of motion were also applied to a large scale state variable control design program, in particular OPTSYS. The resulting control laws were compared with respect to their relative responses, ease of application, and meeting the desired performance objectives.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-149280
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
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