Abstract
This article gives an overview of the compressibility effects, free-stream Mach number and wall temperature effects, on boundary layer laminar-turbulent transition from incompressible flow to low supersonic Mach number (0 < M e < 2). Distinction will be made between ‘natural’ and ‘bypass’ transitions. For boundary layers developing on ‘perfect smooth’ surface in a low free-stream disturbance environment the ‘natural’ transition is induced by modal instabilities and can be predicted using the linear stability theory, in particular the e N method. When the intensity of external disturbances increases (rough surface or high free-stream disturbance), an early ‘bypass’ transition is triggered. This transition is due to the amplification of streaky structures in the laminar zone. This article shows how transient growth theory can be applied to predict the bypass transition induced by 3D roughness elements and how compressibility effects influence such a transition.
Sign-in/Register to access full text options 
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 callMore From: International Journal of Engineering Systems Modelling and Simulation
Disclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
