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. These influence coefficient determined oscillating cascade data were correlated with: (1) data obtained in this cascade with all airfoils oscillating at several interblade phase angle values; and (2) predictions from a classical linearized unsteady cascade model.


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    Title :

    Experimental Investigation of Transonic Oscillating Cascade Aerodynamics


    Contributors:
    D. H. Buffum (author) / S. Fleeter (author)

    Publication date :

    1989


    Size :

    15 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Experimental investigation of transonic oscillating cascade aerodynamics

    Buffum, Daniel H. / Fleeter, Sanford | NTRS | 1989


    Experimental investigation of transonic oscillating cascade aerodynamics

    Buffum, Daniel H. / Fleeter, Sanford | NTRS | 1989



    Experimental investigation of oscillating cascade aerodynamics

    Buffum, Daniel H. / Fleeter, Sanford | NTRS | 1990