Abstract
This work is devoted to the study of the influence of the small angles of attack and external disturbances on the position of the laminar-turbulent transition in the supersonic boundary layer on swept wings. The experiments were carried out in a low-noise supersonic wind tunnel T-325 of the ITAM SB RAS at Mach numbers M = 2 and M = 2.5 on two wing models with leading edge swept angles χ = 45˚ and χ = 72˚. The measurements were carried out by the hot-wire probe or Pitot tube. External disturbances were generated by a wire placed ahead of the nozzles in the subsonic part of the flow. It was shown that external disturbances and small angles of attack strongly affect the position of the laminar-turbulent transition. The laminar-turbulent transition on a wing model with a subsonic leading edge occurs earlier than on a wing model with a supersonic leading edge at low noise conditions. The influence of leading edge swept angle χ on transition Reynolds number was not observed at noisy conditions.
Published Version (
Free)
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call