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  • 1
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    Experimental investigation of oscillating cascade aerodynamics (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A series of experiments are performed in the NASA Lewis Transonic Oscillating Cascade Facility to provide fundamental data quantifying the high subsonic and transonic steady and oscillating aerodynamics of a biconvex airfoil cascade at realistic reduced frequency values for all interblade phase angles. This is accomplished by developing and utilizing an unsteady aerodynamic influence-coefficient technique in which only one cascaded airfoil is oscillated at a time. The vector summation of the resulting airfoil-surface unsteady pressures (measured on a dynamically instrumented airfoil) makes it possible to determine the unsteady aerodynamics of an equivalent cascade with all airfoils oscillating at any specified interblade phase angle.
    Keywords: AERODYNAMICS
    Type: Journal of Aerospace Power (ISSN 1000-8055); 5; 275-282
    Format: text
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  • 2
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    Oscillating cascade aerodynamics by an experimental influence coefficient technique (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 6; 612-620
    Format: text
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  • 3
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    Oscillating Cascade Aerodynamics at Large Mean Incidence Angles (1997)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: In a cooperative program with Pratt & Whitney, researchers obtained fundamental separated flow unsteady aerodynamic data in the NASA Lewis Research Center's Oscillating Cascade. These data fill a void that has hindered the understanding and prediction of subsonic and transonic stall flutter. For small-amplitude torsional oscillations, unsteady pressure distributions were measured on airfoils with cross sections representative of an advanced, low-aspect-ratio fan blade. Data were obtained for two mean incidence angles with a subsonic inflow. At high mean incidence angles (alpha = 10 deg), the mean flow separated at the leading edge and reattached at about 40 percent of the chord. For comparison purposes, data were also obtained for a low incidence angle (a = 0 deg) attached flow.
    Keywords: Aerodynamics
    Type: Research and Technology 1996; NASA-TM-107350
    Format: text
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  • 4
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    Experimental investigation of transonic oscillating cascade aerodynamics (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Fundamental experiments are performed in the NASA Lewis Transonic Oscillating Cascade Facility to investigate the subsonic and transonic aerodynamics of cascaded airfoils executing torsion mode oscillations at realistic values of reduced frequency. In particular, an unsteady aerodynamic influence coefficient technique is developed and utilized. In this technique, only one airfoil in the cascade is oscillated at a time, with the resulting airfoil surface unsteady pressure distribution measured on one dynamically-instrumented reference airfoil. The unsteady aerodynamics of an equivalent cascade with all airfoils oscillating at any specified interblade phase angle are then determined through a vector summation of these data.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 89-0321
    Format: text
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  • 5
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    Investigation of oscillating cascade aerodynamics by an experimental influence coefficient technique (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Fundamental experiments are performed in the NASA Lewis Transonic Oscillating Cascade Facility to investigate the torsion mode unsteady aerodynamics of a biconvex airfoil cascade at realistic values of the reduced frequency for all interblade phase angles at a specified mean flow condition. In particular, an unsteady aerodynamic influence coefficient technique is developed and utilized in which only one airfoil in the cascade is oscillated at a time and the resulting airfoil surface unsteady pressure distribution measured on one dynamically instrumented airfoil. The unsteady aerodynamics of an equivalent cascade with all airfoils oscillating at a specified interblade phase angle are then determined through a vector summation of these data. These influence coefficient determined oscillation cascade data are correlated with data obtained in this cascade with all airfoils oscillating at several interblade phase angle values. The influence coefficients are then utilized to determine the unsteady aerodynamics of the cascade for all interblade phase angles, with these unique data subsequently correlated with predictions from a linearized unsteady cascade model.
    Keywords: AERODYNAMICS
    Type: NASA-TM-101313 , E-4308 , NAS 1.15:101313 , AIAA PAPER 88-2815
    Format: application/pdf
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  • 6
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    Investigation of oscillating cascade aerodynamics by an experimental influence coefficient technique (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Fundamental experiments are performed in the NASA Lewis Transonic Oscillating Cascade Facility to investigate the torsion mode unsteady aerodynamics of a biconvex airfoil cascade at realistic values of the reduced frequency for all interblade phase angles at a specified mean flow condition. In particular, an unsteady aerodynamic influence coefficient technique is developed and utilized in which only one airfoil in the cascade is oscillated at a time and the resulting airfoil surface unsteady pressure distribution measured on one dynamically instrumented airfoil. The unsteady aerodynamics of an equivalent cascade with all airfoils oscillating at a specified interblade phase angle are then determined through a vector summation of these data. These influence coefficient determined oscillating cascade data are correlated with data obtained in this cascade with all airfoils oscillating at several interblade phase angle values. The influence coefficients are then utilized to determine the unsteady aerodynamics of the cascade for all interblade phase angles, with these unique data subsequently correlated with predictions from a linearized unsteady cascade model.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 88-2815
    Format: text
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  • 7
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    Unsteady aerodynamics of an oscillating cascade in a compressible flow field (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Fundamental experiments were performed in the NASA Lewis Transonic Oscillating Cascade Facility to investigate and quantify the unsteady aerodynamics of a cascade of biconvex airfoils executing torsion-mode oscillations at realistic reduced frequencies. Flush-mounted, high-response miniature pressure transducers were used to measure the unsteady airfoil surface pressures. The pressures were measured for three interblade phase angles at two inlet Mach numbers, 0.65 and 0.80, and two incidence angles, 0 and 7 deg. The time-variant pressures were analyzed by means of discrete Fourier transform techniques, and these unique data were then compared with predictions from a linearized unsteady cascade model. The experimental results indicate that the interblade phase angle had a major effect on the chordwise distributions of the airfoil surface unsteady pressure, and that reduced frequency, incidence angle, and Mach number had a somewhat less significant effect.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-100219 , E-3830 , NAS 1.15:100219
    Format: application/pdf
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  • 8
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    The unsteady aerodynamics of an oscillating cascade in a compressible flow field (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Fundamental experiments were performed in the NASA Lewis Transonic Oscillating Cascade Facility to investigate and quantify the unsteady aerodynamics of a cascade of biconvex airfoils executing torsion-mode oscillations at realistic reduced frequencies. Flush-mounted, high-response miniature pressure transducers were used to measure the unsteady airfoil surface pressures. The pressures were measured for three interblade phase angles at two inlet Mach numbers, 0.65 and 0.80, and two incidence angles, 0 and 7 deg. The time-variant pressures were analyzed by means of discrete Fourier transform techniques, and these unique data were then compared with predictions from a linearized unsteady cascade model. The experimental results indicate that the interblade phase angle had a major effect on the chordwise distributions of the airfoil surface unsteady pressure, and that reduced frequency, incidence angle, and Mach number had a somewhat less significant effect.
    Keywords: AERODYNAMICS
    Type: Intl. Symposium on Unsteady Aerodynamics and Aeroelasticity of Turbomachines and Propellers; Sept. 6-10, 1987; Aachen; Germany
    Format: text
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  • 9
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    Aerodynamics of a linear oscillating cascade (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The steady and unsteady aerodynamics of a linear oscillating cascade are investigated using experimental and computational methods. Experiments are performed to quantify the torsion mode oscillating cascade aerodynamics of the NASA Lewis Transonic Oscillating Cascade for subsonic inlet flowfields using two methods: simultaneous oscillation of all the cascaded airfoils at various values of interblade phase angle, and the unsteady aerodynamic influence coefficient technique. Analysis of these data and correlation with classical linearized unsteady aerodynamic analysis predictions indicate that the wind tunnel walls enclosing the cascade have, in some cases, a detrimental effect on the cascade unsteady aerodynamics. An Euler code for oscillating cascade aerodynamics is modified to incorporate improved upstream and downstream boundary conditions and also the unsteady aerodynamic influence coefficient technique. The new boundary conditions are shown to improve the unsteady aerodynamic influence coefficient technique. The new boundary conditions are shown to improve the unsteady aerodynamic predictions of the code, and the computational unsteady aerodynamic influence coefficient technique is shown to be a viable alternative for calculation of oscillating cascade aerodynamics.
    Keywords: AERODYNAMICS
    Type: NASA-TM-103250 , E-5677 , NAS 1.15:103250
    Format: application/pdf
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  • 10
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    Effect of wind tunnel acoustic modes on linear oscillating cascade aerodynamics (1993)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The aerodynamics of a biconvex airfoil cascade oscillating in torsion is investigated using the unsteady aerodynamic influence coefficient technique. For subsonic flow and reduced frequencies as large as 0.9, airfoil surface unsteady pressures resulting from oscillation of one of the airfoils are measured using flush-mounted high-frequency-response pressure transducers. The influence coefficient data are examined in detail and then used to predict the unsteady aerodynamics of a cascade oscillating at various interblade phase angles. These results are correlated with experimental data obtained in the traveling-wave mode of oscillation and linearized analysis predictions. It is found that the unsteady pressure disturbances created by an oscillating airfoil excite wind tunnel acoustic modes which have detrimental effects on the experimental data. Acoustic treatment is proposed to rectify this problem.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-106367 , E-8171 , NAS 1.15:106367 , ASME International Gas Turbine and Aeroengine Congress and Exposition; May 24, 1993 - May 27, 1993; Cincinnati, OH; United States
    Format: application/pdf
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