Transition flight experiments on a swept wing with suctionFlight experiments were conducted on a 30 degree swept wing with a perforated leading edge by systematically varying the location and amount of suction over a range of Mach number and Reynolds number. Suction was varied chordwise ahead of the front spar from either the front or rear direction by sealing spanwise perforated strips. 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 the test configuration, flight condition, and suction location. A state-of-the-art linear stability theory which accounts for body and streamline curvature and compressibility was used to study the boundary layer stability as suction location and magnitude varied. N-factor correlations with transition location were made for various suction configurations.
Document ID
19890054744
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Maddalon, D. V. (NASA Langley Research Center Hampton, VA, United States)
Land, C. K. (NASA Langley Research Center Hampton, VA, United States)
Collier, F. S. (High Technology Corp. Hampton, VA, United States)
Montoya, L. C. (NASA Flight Research Center Edwards, CA, United States)