Dual‐mode combustion is characterized by extensive interaction with the flow upstream of the combustor entrance, developing as an oblique shock train with associated low velocity or large recirculation flow adjacent to the walls. The dual‐mode scramjet engine is a unique propulsion system that combines the benefits of subsonic combustion at the lower flight speeds with supersonic combustion in the hypersonic regime. Only a limited amount of heat can be added to the flow in constant area ducts. Most practical scramjet engines include combustor designs with area relief. The thermal throat is a crucial design requirement for practical application of the dual‐mode scramjet. The physics of dual‐mode transition flows are characterized by strong shock trains, complex shock‐boundary layer interactions, significant regions of separated flows, and mixing‐limited chemical reactions. The complexity of reacting flow in the scramjet combustor operating in dual‐mode makes both analysis and design extraordinarily difficult.
Dual‐Mode Combustion Scramjet
Scramjet Propulsion ; 227-249
18.11.2022
23 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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