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 wm 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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    Title :

    Transition Flight Experiments on a Swept Wing With Suction


    Contributors:

    Publication date :

    2004


    Size :

    16 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    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. / Collier, F. S., Jr. / Montoya, L. C. 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

    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