Scaling of an existing 60 kN LOX/LCH4 combustion down to a liquid 2.5 kN HTP/Kerosene combustion of an innovative hyperboloid rocket engine in Ansys Fluent

elib (German Aerospace Center) 2026 Thesis

Authors: Bruno Müller

Cited by: 0

Fields of Study & Subjects

Rocket and propulsion systems research Combustion and flame dynamics Heat transfer and supercritical fluids