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  • 1980-1984  (5)
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  • 1
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    Aerodynamic performances of three fan stator designs operating with rotor having tip speed of 337 meters per second and pressure ratio of 1.54. Relation of analytical code calculations to experimental performance (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A hub-to-shroud and a blade-to-blade internal-flow analysis code, both inviscid and basically subsonic, were used to calculate the flow parameters within four stator-blade rows. The produced ratios of maximum suction-surface velocity to trailing-edge velocity correlated well in the midspan region, with the measured total-parameters over the minimum-loss to near stall operating range for all stators and speeds studied. The potential benefits of a blade designed with the aid of these flow analysis codes are illustrated by a proposed redesign of one of the four stators studied. An overall efficiency improvement of 1.6 points above the peak measured for that stator is predicted for the redesign.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1614 , E-137
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Aerodynamic performances of three fan stator designs operating with rotor having tip speed of 337 meters per second and pressure ratio of 1.54. 1: Experimental performance (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The aerodynamic performances of four stator-blade rows are presented and evaluated. The aerodynamic designs of two of these stators were compromised to reduce noise, a third design was not. On a calculated operating line passing through the design point pressure ratio, the best stator had overall pressure-ratio and efficiency decrements of 0.031 and 0.044, respectively, providing a stage pressure ratio of 1.483 and efficiency of 0.865. The other stators showed some correctable deficiencies due partly to the design compromises for noise. In the end-wall regions blade-element losses were significantly less for the shortest chord studied.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1610 , E-136
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Redesign and cascade tests of a supercritical controlled diffusion stator blade-section (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A supercritical stator blade section, previously tested in cascade, and characterized by a flat-roof-top suction surface Mach number distribution, has been redesigned and retested. At near design conditions, the losses and air turning were improved over the original blade by 50 percent and 7 percent, respectively. The key element in the improved performance was a small blade reshaping. This produced a continuous flow acceleration over the first one-third chord of the suction surface which successfully prevented a premature laminar separation bubble. Several recently available inviscid analysis codes and one fully viscous (Navier-Stokes) analysis code were used in the redesign process. The validity of these codes was enhanced by the test results. Previously announced in STAR as N84-22533
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-1207
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Redesign and cascade tests of a supercritical controlled diffusion stator blade-section (1984)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A supercritical stator blade section, previously tested in cascade, and characterized by a flat-roof-top suction surface Mach number distribution, has been redesigned and retested. At near design conditions, the losses and air turning were improved over the original blade by 50 percent and 7 percent respectively. The key element in the improved performance was a small blade reshaping. This produced a continuous flow acceleration over the first one-third chord of the suction surface which successfully prevented a premature laminar separation bubble. Several recently available inviscid analysis and one fully viscous (Navier-Stokes) analysis code were used in the redesign process. The validity of these codes was enhanced by the test results.
    Keywords: AERODYNAMICS
    Type: NASA-TM-83635 , E-2077 , NAS 1.15:83635 , Joint Propulsion Conf.; Jun 11, 1984 - Jun 13, 1984; Cincinnati, OH; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Design and performance of a fixed, nonaccelerating, guide vane cascade that operates over an inlet flow angle range of 60 deg (1984)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A unique set of wind tunnel guide vanes are designed with an inverse design code and analyzed with a panel method and an integral boundary layer code developed at the NASA Lewis Research Center. The fixed guide vanes, 80 feet long with 6-foot chord length, were designed for the NASA Ames 40 x 80/80 x 120 ft Wind Tunnel. Low subsonic flow is accepted over a 60 deg range of inlet angle from either the 40 x 80 leg or the 80 x 120 leg of the wind tunnel, and directed axially into the main leg of the tunnel where drive fans are located. Experimental tests of 1/10-scale models were conducted to verify design calculations.
    Keywords: AERODYNAMICS
    Type: NASA-TM-83519 , E-1868 , NAS 1.15:83519 , Ann. Intern. Gas Turbine Conference; Jun 03, 1984 - Jun 07, 1984; Amsterdam
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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