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  • 1
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    Analysis of distortion data from TF30-P-3 mixed compression inlet test (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A program was conducted to reduce and analyze inlet and engine data obtained during testing of a TF30-P-3 engine operating behind a mixed compression inlet. Previously developed distortion analysis techniques were applied to the data to assist in the development of a new distortion methodology. Instantaneous distortion techniques were refined as part of the distortion methodology development. A technique for estimating maximum levels of instantaneous distortion from steady state and average turbulence data was also developed as part of the program.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2686
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    A method of distortion pattern synthesis for high response data screening (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An empirically derived method of estimating maximum levels of instantaneous inlet total pressure distortion from steady state measurements is presented. The estimation procedure uses steady state total pressure and root mean square turbulent pressure data measurements to synthesize instantaneous distortion patterns. The synthesis method is tailored to intensify distortion patterns in a manner consistent with the characteristics of the particular index to be used in evaluating inlet/engine compatability. The maximum expected value of distortion, a statistically determined function of the length of time of inlet operation, is used to constrain the amount of pattern intensification. Comparison with an independent set of data is presented for verification of the synthesis method.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 76-704 , Propulsion Conference; Jul 26, 1976 - Jul 29, 1976; Palo Alto, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    An improved analytical model of the separation region on boattail nozzles at subsonic speeds (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A practical engineering calculation was developed to model the viscous effects of a separated, reverse flow region on afterbody pressures and drag. This viscous calculation was iteratively coupled with an inviscid flow calculation by means of an aerodynamic interface. A standard boundary layer displacement thickness was used to modify the afterbody shape where the flow was attached. A discriminating streamline calculation was developed to account for displacement effects of the reverse flow in separated regions with and without a flowing jet. The viscous flow calculation was coupled with a potential flow calculation. The analysis accurately predicted afterbody pressures and drag with variations in Reynolds number, Mach number, and afterbody shape.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3028 , PWA-5599
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    An improved analytical model of the separated region on nozzle boattails (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A viscous flow calculation is formulated for modelling the effects of separated, reverse flow regions on nozzle afterbody pressures and drags at subsonic Mach numbers. A discriminating streamline approach is used. Effects of skin friction, axial pressure gradient, and nozzle jet entrainment on the separated discriminating streamline shape are included. The viscous flow calculation is coupled to a potential flow calculation. The combined analysis is found to accurately predict both the magnitude of the measured afterbody pressures and drag, and also their variation with Reynolds number, Mach number and afterbody shape.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 78-995 , Joint Propulsion Conference; Jul 25, 1978 - Jul 27, 1978; Las Vegas, NV; US
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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