Transition flight experiments on a swept wing with suctionFlight 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.
Document ID
19890066459
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Maddalon, D. V. (NASA Langley Research Center Hampton, VA, United States)
Collier, F. S., Jr. (High Technology Corp. Hampton, VA, United States)
Montoya, L. C. (NASA Flight Research Center Edwards, CA, United States)
Putnam, R. J. (PRC Kentron, Inc. Hampton, VA, United States)