Flight boundary-layer transition experiments were conducted on a 30-degree swept wing with a perforated leading-edge suction panel. The transition location on the panel was changed by systematically varying the location and amount of suction. Transition from laminar to turbulent flow was due to leading-edge turbulence contamination or crossflow disturbance growth and/or Tollmien-Schlichting disturbance growth, depending on flight condition and suction variation. Amplification factor correlations with transition location were made for various suction configurations using a state-of-the-art linear stability theory which accounts for body and streamline curvature and compressibility.


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    Titel :

    Transition flight experiments on a swept wing with suction


    Beteiligte:
    Maddalon, D. V. (Autor:in) / Collier, F. S., Jr. (Autor:in) / Montoya, L. C. (Autor:in) / Putnam, R. J. (Autor:in)

    Erscheinungsdatum :

    1989-09-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Transition flight experiments on a swept wing with suction

    MADDALON, D. / LAND, C. / COLLIER, F. et al. | AIAA | 1989


    Transition flight experiments on a swept wing with suction

    Maddalon, D. V. / Land, C. K. / Collier, F. S. et al. | NTRS | 1989


    Transition Flight Experiments on a Swept Wing with Suction

    Maddalon, D. V. / Collier, F. S., Jr. / Montoya, L. C. et al. | NTRS | 1989


    Transition Flight Experiments on a Swept Wing With Suction

    D. V. Maddalon / F. S. Collier / L. C. Montatoya et al. | NTIS | 2004


    Transition Flight Experiments on a Swept Wing With Suction

    Maddalon, D. V. / Collier, F. S., Jr. / Montoya, L. C. et al. | NTRS | 1989