Abstract
In the present study, the concept of forward facing flap mounted on a slender delta wing, originally proposed by Hurley is considered. The test model resulted in surfaces that deflected from the basic delta to form a simple X-configuration. With this configuration, force balance measurements were conducted at low speed in a low speed open circuit wind tunnel. The lift produced was found to be dependent on both the flap deflection angle and thickness. Overall, the results obtained are very promising as they show definitive trends in the lift performance improvement of the X-configuration over conventional base delta wing at low angles of attack.
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 Review of Aerospace Engineering (IREASE)
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.
