Effect of shock generator on fuel mixing in an annular single lobe transverse nozzle at the supersonic combustion chamber of a scramjet engine using computational fluid dynamics
Dechen Wei, Yuanyuan Jiao, Ning Zhang, Yukun Fan
Topics & Concepts
ScramjetSupersonic speedCombustionCombustion chamberNozzleComputational fluid dynamicsMechanicsCombustorNuclear engineeringAerospace engineeringEngineeringMaterials scienceMechanical engineeringPhysicsChemistryOrganic chemistryComputational Fluid Dynamics and AerodynamicsRocket and propulsion systems research