The supersonic double wedge airfoil performs quite excellent in the supersonic speed regime but would lead to poor performance at subsonic speed regime due to sharp edges stall. For this purpose a theoretical and experimental study was undertaken to improve performance characteristics of the supersonic double wedge airfoil at low speed by using passive-active flow controlling methods. The proposed passive method was a shape modification through changing the sharp leading edge and mid-section upperand lower surface apex to smooth curved control segment actived during subsonic flight regime; and the blowing technique was used as an active method. ANSYS FLUENT CFD package was used to simulate the flow around the standard and modified airfoils. Low speed wind tunnel tests were also conducted in order to measure pressures and velocities chordal-wise the model airfoils fabricated to accomplish these wind tunnel tests.The results had proven that theproposed flow controlling methods had improved the performance of the double wedge airfoil at low speed. The maximum lift coefficient πΆ π,πππ₯ was increased by about (38%) and the stall angle for πΆ π,πππ₯ was jumped from ( 12Β°) for the standard airfoil to ( 18Β°) for the modified airfoil with blowing. The experimental results coincide well with the theoretical results.
scite is a Brooklyn-based organization that helps researchers better discover and understand research articles through Smart Citationsβcitations that display the context of the citation and describe whether the article provides supporting or contrasting evidence. scite is used by students and researchers from around the world and is funded in part by the National Science Foundation and the National Institute on Drug Abuse of the National Institutes of Health.
hi@scite.ai
10624 S. Eastern Ave., Ste. A-614
Henderson, NV 89052, USA
Copyright Β© 2024 scite LLC. All rights reserved.
Made with π for researchers
Part of the Research Solutions Family.