Baza Publikacji Pracowników Politechniki Lubelskiej

Status:
Autorzy:	John Bibin, Dinesan Deepu, Gęca Michał Jan, M. S. Srijith
Dyscypliny:
	Aby zobaczyć szczegóły należy się zalogować.
Rok wydania:	2024
Wersja dokumentu:	Elektroniczna
Język:	angielski
Wolumen/Tom:	283
Numer artykułu:	106397
Strony:	1 - 17
Impact Factor:	2,5
Web of Science® Times Cited:	1
Scopus® Cytowania:	1
Bazy:	Web of Science \| Scopus
Efekt badań statutowych	NIE
Finansowanie:	This research was supported by the Polish National Agency for Academic Exchange (NAWA), through the Ulam NAWA fellowship (BPN/ULM/2022/1/00146) awarded to the first author.
Materiał konferencyjny:	NIE
Publikacja OA:	NIE
Abstrakty:	angielski
	Shock Wave Boundary Layer Interactions (SWBLI) occur due to the convergence of a shock wave and a viscous boundary layer. The resulting separation bubble is a major setback for the performance of high-speed air intakes. This paper presents a numerical investigation into the potential of a Pressure Feedback Technique (PFT) to alleviate shock-induced flow separation within a Scramjet engine intake operating at Mach 4. The PFT is a novel self-sustaining flow control technique that combines simultaneous suction and injection. The two main output parameters used to support the hypothesis of the present study are the size of the separation bubble as well as the total pressure recovery at the isolator outlet. The most prominent observation of this study is that with the installation of the PF tubes, the total pressure recovery at the exit is noted to rise. The effectiveness of the pressure feedback technique in reducing the intensity of the separation bubbles is found to depend on the diameter of the PFT, pitch-to-diameter ratio, and PFT tube design.

Informacja o cookies

Pressure feedback system for flow separation mitigation in scramjet intakes

Artykuł w czasopiśmie