The development of a hypersonic air‐breathing aircraft relies heavily on the optimal integration of the engine and the airframe. Scramjet cycle performance requires that the single expansion ramp nozzle exhaust cross section be about 30% larger than the inlet capture cross‐sectional area. In all hypersonic flight applications, the supersonic nozzle must be designed to optimize thrust, while at the same time aiming to reduce airframe weight at large expansion ratios, reduce drag, increase controllability with thrust vectoring, and offer high operational reliability. Several 3‐D asymmetric scramjet nozzles were developed using streamline tracing and hybrid optimization strategies. Today, computational fluid dynamics (CFD) provides the most powerful tools that researchers and industry are undertaking. The preliminary design of the scramjet nozzle/afterbody section using CFD analysis is economical and effective. Ground testing a scramjet nozzle‐afterbody section using the actual engine combustion products is challenging if not impossible in a conventional wind tunnel.
Scramjet Nozzle/Aftbody
Scramjet Propulsion ; 251-277
18.11.2022
27 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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