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In conventional spacecraft propulsion systems (rockets), the oxidiser needed for combustion comprises a major proportion of the initial mass (approx. 70%). There is therefore considerable interest in air-breathing engines that use the oxygen in the air for combustion at flight mach numbers in the range Ma=15…20. In this case, flow through the combustion chamber must occur at supersonic speed, while mixing and combustion must be accomplished in an extremely short time. Theoretical numerical studies on such scramjets (supersonic combustion ramjets) are carried out at the Institute. 3D simulation methods are available with which compressible flows can be computed with detailed chemistry, taking turbulence-chemistry interaction into account. These studies range from various type of fuel injection, to pollutant emission aspects and wall heat loads in the combustion chamber.