Abstract
The paper is devoted to an experimental study of natural disturbances evolution and laminar-turbulent transition in a three-dimensional supersonic boundary layer on swept wing at different Mach numbers. Characteristic zones of disturbances evolution are determined. It is found that for Mach numbers 2 and 2.5 measurements were performed in the region of linear stage of disturbances evolution, and the experimental data can be compared with the results of the calculations on linear stability theory. Oscillograms, amplitude-frequency spectra, pulsation profiles and statistical diagrams of natural fluctuations are obtained. Secondary instability of supersonic boundary layer on swept wing is under consideration
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 callDisclaimer: 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.
