[A-4] Combustion

[2022-a-18] Flame Characteristics of a High-Pressure LOX/CNG Rocket Combustor with Large Optical
Access

*Jan Martin¹, Wolfgang Armbruster¹, Dmitry Suslov¹, Robert Stützer¹, Justin Hardi¹, Michael Oschwald^1,2 (1. German Aerospace Center (DLR), Institute of Space Propulsion, 2. RWTH Aachen University, Institute of Jet Propulsion and Turbomachinery)

Keywords:rocket engine, sub-/supercritical combustion, optical access, liquid oxygen / compressed natural gas, single-injector