Bora O. Cakir, Ali Can Ispir, Bayindir H. Saracoglu
DOI Number XXX-YYY-ZZZ
Conference Number HiSST-2022-408
Ramjet/scramjet propulsion is commonly preferred to power supersonic & hypersonic vehicles for cruis-
ing faster than Mach 3. This is an elegant solution owing to the lean architecture which does not embody
any rotating parts. Although the geometry of the engine is simple as compared to turbo-based engines,
the flow physics through the engine duct is quite complex and, the flow speeds modulate between the
supersonic and subsonic regimes. The design and performance analysis of such engine configura-
tions are vital to make sure that propulsion systems can satisfy the flight trajectory requirements. In the
present study, a low fidelity design and analysis methodology is introduced to investigate the propulsive
performance characterizations of different design choices on intake configurations, providing complete
propulsive flow path simulations via subsonic combustion, thermal choke phenomena and ideal expan-
sion through the nozzle.