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Modelling a Hypersonic Single Expansion Ramp Nozzle of a Hypersonic Aircraft through Parametric Studies

College of Engineering, Design and Physical Sciences, Brunel University London, London UB8 3PH, UK
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Energies 2018, 11(12), 3449; https://doi.org/10.3390/en11123449
Received: 26 September 2018 / Revised: 3 December 2018 / Accepted: 7 December 2018 / Published: 10 December 2018
This paper aims to contribute to developing a potential combined cycle air-breathing engine integrated into an aircraft design, capable of performing flight profiles on a commercial scale. This study specifically focuses on the single expansion ramp nozzle (SERN) and aircraft-engine integration with an emphasis on the combined cycle engine integration into the conceptual aircraft design. A parametric study using computational fluid dynamics (CFD) have been employed to analyze the sensitivity of the SERN’s performance parameters with changing geometry and operating conditions. The SERN adapted to the different operating conditions and was able to retain its performance throughout the altitude simulated. The expansion ramp shape, angle, exit area, and cowl shape influenced the thrust substantially. The internal nozzle expansion and expansion ramp had a significant effect on the lift and moment performance. An optimized SERN was assembled into a scramjet and was subject to various nozzle inflow conditions, to which combustion flow from twin strut injectors produced the best thrust performance. Side fence studies observed longer and diverging side fences to produce extra thrust compared to small and straight fences. View Full-Text
Keywords: scramjet; single expansion ramp nozzle; hypersonic aircraft; combined cycle engines scramjet; single expansion ramp nozzle; hypersonic aircraft; combined cycle engines
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MDPI and ACS Style

Ridgway, A.; Sam, A.A.; Pesyridis, A. Modelling a Hypersonic Single Expansion Ramp Nozzle of a Hypersonic Aircraft through Parametric Studies. Energies 2018, 11, 3449.

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