Open AccessShock Waves Analysis of the Novel Intake Design System for a Scramjet Propulsion
Author(s) -
Abdulla Khamis Alhassani,
Mohanad Tarek Mohamed,
Mohammed Fares,
Sharul Sham Dol
Publication year - 2021
Publication title -
wseas transactions on systems
Language(s) - English
Resource type - Journals
eISSN - 2224-2678
pISSN - 1109-2777
DOI - 10.37394/23202.2021.20.9
Subject(s) - scramjet , supersonic speed , aerospace engineering , ramjet , mach number , propulsion , shock wave , oblique shock , combustion , hypersonic speed , gas compressor , shock (circulatory) , aerospace , materials science , engineering , combustor , chemistry , medicine , organic chemistry
The supersonic combustion scramjet in the inlet applies the shock waves compression mechanism tosubstitute the actual compressor from a gas turbine engine. The scramjet works with combustion of fuel throughthe air stream in supersonic condition at least with Mach 5. Novel design of a scramjet intake system was madewith variations in the angle of the fins and entrance width. The best combination of diameter and inclinationangle was 1.75 m and 15 degrees, respectively. The findings were able to increase the oblique shock waveinteractions and supplicate effective combustion and reduce pressure losses for the effective application ofscramjet system, which can be significant for aerospace industry.