Abstract
Purpose – The main purpose of this research is to investigate distortion and duct total pressure loss at the duct exit (engine face) of a special S-shaped air intake at different simulated flight regimes with and without lip-screen installation. This air intake is supposed to be equipped with a micro jet engine. Design/methodology/approach – Experimental investigations were performed by using a low subsonic close loop wind tunnel to simulate different flight regimes such as negative stall, cruise, shallow angle climb, steep angle climb and positive stall. In order to investigate flow behaviour along the duct length, static pressure changes were also measured. Test results were plotted in terms of total pressure contours and reduced results were tabulated. Static pressure results were also illustrated in different figures. Findings – Results indicated that duct total pressure loss is within the acceptable range and is less than the 2 percent (allowable value) at various flight regimes, but installation of ...
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 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.
