Abstract
Studies of flow structure near the surface model of drones have been conducted in the subsonic wind tunnel. Experimental data of flow visualization depending on attack angle were obtained by oil film method. Evolution of flow patterns inside the regions of boundary layer separation in different configurations was demonstrated. Ability of separation control and reduction zones of flow separation by local influence (ribs and cones) has been also studied on the wing surface.
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.
