AbstractA new Re-cooled Cycle has been proposed for a regeneratively cooled scramjet to reduce the fuel flow for cooling, fuel heat sink (cooling capacity) is repeatedly used to indirectly increase the fuel heat sink, and fuel onboard is adequate to satisfy the cooling requirement for the whole hypersonic vehicle. Parametric analysis of the Re-cooled Cycle carried out in previous study shows the potential for the cycle to be optimized. A thermodynamic optimization analysis of Re-cooled Cycle for a scramjet is obtained by satisfying hydrodynamic, thermal, and Mach number constraints. The optimal cycle parameters and length allocation between the first and second cooling passages are obtained.
Thermodynamic optimization for a scramjet with Re-cooled Cycle
Acta Astronautica ; 66 , 9-10 ; 1449-1457
2009-11-01
9 pages
Article (Journal)
Electronic Resource
English
Thermodynamic optimization for a scramjet with Re-cooled Cycle
Online Contents | 2010
|Irreversible cycle analysis of a re-cooled cycle for a scramjet
SAGE Publications | 2010
|Irreversible cycle analysis of a re-cooled cycle for a scramjet
Tema Archive | 2010
|Irreversible cycle analysis of a re-cooled cycle for a scramjet
Online Contents | 2010
|Cooled CMC Scramjet Combustor Structure Development
AIAA | 2002
|