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  • 1
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    Analysis of an unswept propfan blade with a semiempirical dynamic stall model (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The time history response of a propfan wind tunnel model with dynamic stall is studied analytically. The response obtained from the analysis is compared with available experimental data. The governing equations of motion are formulated in terms of blade normal modes which are calculated using the COSMIC-NASTRAN computer code. The response analysis considered the blade plunging and pitching motions. The lift, drag and moment coefficients for angles of attack below the static stall angle are obtained from a quasi-steady theory. For angles above static stall angles, a semiempirical dynamic stall model based on a correction to angle of attack is used to obtain lift, drag and moment coefficients. Using these coefficients, the aerodynamic forces are calculated at a selected number of strips, and integrated to obtain the total generalized forces. The combined momentum-blade element theory is used to calculate the induced velocity. The semiempirical stall model predicted a limit cycle oscillation near the setting angle at which large vibratory stresses were observed in an experiment. The predicted mode and frequency of oscillation also agreed with those measured in the experiment near the setting angle.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-4083 , E-4196 , NAS 1.15:4083
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Propfan Test Assessment (PTA): Flight test report (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Propfan Test Assessment (PTA) aircraft was flown to obtain glade stress and noise data for a 2.74m (9 ft.) diameter single rotation propfan. Tests were performed at Mach numbers to 0.85 and altitudes to 12,192m (40,000 ft.). The propfan was well-behaved structurally over the entire flight envelope, demonstrating that the blade design technology was completely adequate. Noise data were characterized by strong signals at blade passage frequency and up to 10 harmonics. Cabin noise was not so high as to preclude attainment of comfortable levels with suitable wall treatment. Community noise was not excessive.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-182278 , NAS 1.26:182278 , LG89ER0026
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Mach 5 inlet CFD and experimental results (1989)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An experimental research program was conducted in the NASA Lewis Research Center 10 x 10 ft supersonic wind tunnel. The 2-D inlet model was designed to study the Mach 3.0 to 5.0 speed range for an over-under turbojet plus ramjet propulsion system. The model was extensively instrumented to provide both analytical code validation data as well as inlet performance information. Support studies for the program include flow field predictions with both 3-D parabolized Navier-Stokes (PNS) and 3-D full Navier-Stokes (FNS) analytical codes. Analytical predictions and experimental results are compared.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-102317 , E-5011 , NAS 1.15:102317 , AIAA PAPER 89-2355 , Joint Propulsion Conference; Jul 10, 1989 - Jul 12, 1989; Monterey, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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