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  • 1
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    Turbofan blade stresses induced by the flow distortion of a VTOL inlet at high angles of attack (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A 51-cm-diameter turbofan with a tilt-nacelle VTOL inlet was tested in the Lewis Research Center's 9- by 15-Ft Low Speed Wind Tunnel at velocities up to 72 m/s and angles of attack up to 120 deg. Fan-blade vibratory stress levels were investigated over a full aircraft operating range. These stresses were due to inlet air flow distortion resulting from (1) internal flow separation in the inlet, and (2) ingestion of the exterior nacelle wake. Stress levels are presented, along with an estimated safe operating envelope, based on infinite blade fatigue life.
    Keywords: AERODYNAMICS
    Type: NASA-TM-82963 , E-1380 , NAS 1.15:82963
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Low speed testing of the inlets designed for a tandem-fan V/STOL nacelle (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An approximately 0.25 scale model of a tandem fan nacelle, designed for a subsonic V/STOL aircraft, was tested in a Lewis wind tunnel. Model variables included long and short aft inlet cowls and the addition of exterior strakes to the short inlet cowl. Inlet pressure recoveries and distortion were measured at pitch angles to 40 deg and at combinations of pitch and yaw to 30 deg. Airspeeds covered a range to 135 knots (69 m/sec). The short aft inlet with added strakes had the best aerodynamic performance and is considered suitable for the intended V/STOL application.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 81-2627 , V/STOL Conference; Dec 07, 1981 - Dec 09, 1981; Palo Alto, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    VSTOL tilt nacelle aerodynamics and its relation to fan blade stresses (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A scale model of a VSTOL tilt nacelle with a 0.508 m single stage fan was tested in the NASA Lewis 9x15 Low Speed Wind Tunnel to ascertain inlet aerodynamic and fan aeromechanical performance over the low speed flight envelope. Fan blade stress maxima occurred at discrete rotational speeds corresponding to integral engine order vibrations of the first flatwise bending mode. Increased fan blade stress levels coincided with internal boundary layer separation occurring but became severe only when the separation location had progressed to the entry lip region of the inlet. The inlet/fan system could operate within the low speed flight envelope without incurring fan blade stress limits although boundary layer separation did occur for certain operating conditions.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 78-958 , Joint Propulsion Conference; Jul 25, 1978 - Jul 27, 1978; Las Vegas, NV; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    VSTOL tilt nacelle aerodynamics and its relation to fan blade stresses (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A scale model of a VSTOL tilt nacelle with a 0.508 m single stage fan was tested in a low speed wind tunnel to ascertain inlet aerodynamic and fan aeromechanical performance over the low speed flight envelope. Fan blade stress maxima occurred at discrete rotational speeds corresponding to integral engine order vibrations of the first flatwise bending mode. Increased fan blade stress levels coincided with internal boundary layer separation but became severe only when the separation location had progressed to the entry lip region of the inlet.
    Keywords: AERODYNAMICS
    Type: NASA-TM-78899 , E-9635 , Joint Propulsion Conf.; Jul 25, 1978 - Jul 27, 1978; Las Vegas, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Performance of a V/STOL tilt nacelle inlet with blowing boundary layer control (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A scale model of a V/STOL tilt nacelle fitted to a 0.508 m single stage fan was tested in the NASA Lewis low speed wind tunnel to determine the effect of diffuser blowing on the inlet aerodynamics and aeromechanical performance. The test was conducted over a range of freestream speeds (up to 120 knots) and angles-of attack (up to 120 deg). In general, diffuser blowing had a beneficial affect on all performance parameters. The angle-of-attack range for a separation-free flow substantially increased, and the fan face distortion reduced with a corresponding increase in total pressure recovery. Discrete narrow band blade stress peaks which were common to the nonblowing (baseline) configuration were eradicated with diffuser blowing.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 79-1163 , AIAA, SAE, and ASME, Joint Propulsion Conference; Jun 18, 1979 - Jun 20, 1979; Las Vegas, NV
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 6
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    Low speed testing of the inlets designed for a tamden-fan V/STOL nacelle (1981)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An approximately 0.25 scale model of a tandem fan nacelle, designed for a subsonic V/STOL aircraft, was tested in a Lewis wind tunnel. Model variables included long and short aft inlet cowls and the addition of exterior strakes to the short inlet cowl. Inlet pressure recoveries and distortion were measured at pitch angles to 40 deg and at combinations of pitch and yaw to 30 deg. Airspeeds covered a range to 135 knots (69 m/sec). The short aft inlet with added strakes had the best aerodynamic performance and is considered suitable for the intended V/STOL application.
    Keywords: AERODYNAMICS
    Type: NASA-TM-82728 , E-1031 , AIAA PAPER 81-2627 , V/STOL Conf.; Dec 07, 1981 - Dec 09, 1981; Palo Alto, CA; United States
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 7
    facet.materialart.
    Unknown
    Performance of a V/STOL tilt nacelle inlet with blowing boundary layer control (1979)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A scale model of a V/STOL tilt nacelle fitted to a 0.508 m single stage fan was tested in the NASA Lewis 9x15 ft low speed wind tunnel to determine the effect of diffuser blowing on the inlet aerodynamics and aeromechanical performance. The test was conducted over a range of freestream speeds (up to 120 knots) and angles of attack (up to 120 deg). Diffuser blowing had a beneficial affect on all performance parameters. The angle of attack range for separation free flow substantially increased, and the fan face distortion significantly reduced with a corresponding increase in total pressure recovery. Discrete narrow band blade stress peaks which were common to the nonblowing (baseline) configuration were eradicated with diffuser blowing.
    Keywords: AERODYNAMICS
    Type: NASA-TM-79176 , E-043 , Joint Propulsion Conf.; Jun 18, 1979 - Jun 20, 1979; Las Vegas, NV; United States
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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