A flutter model, consisting of a wing, horizontal tail, and splitter plate/fuselage mechanism, was tested in a 4-foot transonic tunnel in the Mach number range 1.1 to 1.3. Two types of flutter were encountered during the testing: a wing-tail flutter bending-torsion flutter mode. The wing-tail flutter speed was found to be a minimum at M = 1.2 for the configuration tested. Recorded model test data were digitized for a power spectral density (PSD) analysis and Random Decrement (Randomdec) analysis. Comparisons between the frequency and damping obtained from the PSD plots and the Randomdec signatures agreed very well. A limited flutter analysis was conducted using a Mach box unsteady aerodynamics method which accounted for interference and airfoil thickness. Analytical comparisons with experimental flutter speeds agreed well. The analyses assuming zero thickness predicted flutter speeds higher than those measured, ranging from 1 percent at M = 1.12 to 8 percent at M = 1.28. With the airfoil thickness included, the correlation was improved such that predicted flutter speeds for all cases investigated were within 2 percent of experimental speeds.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Wind tunnel investigation of supersonic wing-tail flutter


    Contributors:


    Publication date :

    1976-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Investigation of wing flutter in the wind tunnel

    Essers, I. | Engineering Index Backfile | 1929



    Wing-tail interaction flutter revisited

    Yurkovich, R. | Tema Archive | 1996


    Wing-Tail Interaction Flutter Revisited

    Yurkovich, R. / AIAA / ASME et al. | British Library Conference Proceedings | 1996


    Wing-tail interaction flutter revisited

    Yurkovich, Rudy | AIAA | 1996