Supersonic Combustion

05.01.2012

Cruising at very high speeds such as 8 times the speed of sound requires new type of propulsion systems. Research on supersonic combustion ramjet, scramjet, is carried out in international cooperation by flight experiments, wind tunnel and CFD.

Photo of the intake and combustion chamber of the HySHOT flight experiment on top of a sounding rocket at the launch pad

HySHOT flight reconstruction in the high enthalpy shock-tunnel Göttingen (HEG);
Photo of the wind tunnel model

CFD assessment of the EU-Lapcat Mach 8 engine; Mach number contours and isobars along compression ramp, intake and combustion chamber.

Numerical simulation of a combustion process;
Contours of temperature (top) and combustion products (bottom) inside the combustion chamber and streamlines emanating from a planar injector

Investigation of a Hypermixer type of injector in the high enthalpy shock-tunnel Göttingen HEG (top) and using CFD (bottom)

Contact

Sebastian Karl
German Aerospace Center
Institute of Aerodynamics and Flow Technology, Spacecraft
Göttingen
Tel.: +49 551 709-2848
Fax: +49 551 709-2800

Department Spacecraft (AS-RFZ)

Propellants and Fuels

Fluid Mechanics and Thermodynamics