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

Author

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  • Andrew Ridgway

    (College of Engineering, Design and Physical Sciences, Brunel University London, London UB8 3PH, UK)

  • Ashish Alex Sam

    (College of Engineering, Design and Physical Sciences, Brunel University London, London UB8 3PH, UK)

  • Apostolos Pesyridis

    (College of Engineering, Design and Physical Sciences, Brunel University London, London UB8 3PH, UK)

Abstract

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.

Suggested Citation

  • Andrew Ridgway & Ashish Alex Sam & Apostolos Pesyridis, 2018. "Modelling a Hypersonic Single Expansion Ramp Nozzle of a Hypersonic Aircraft through Parametric Studies," Energies, MDPI, vol. 11(12), pages 1-29, December.
    • Handle: RePEc:gam:jeners:v:11:y:2018:i:12:p:3449-:d:189265
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    References listed on IDEAS

    as
    1. Stephen M. Neill & Apostolos Pesyridis, 2017. "Modeling of Supersonic Combustion Systems for Sustained Hypersonic Flight," Energies, MDPI, vol. 10(11), pages 1-22, November.
    2. Devendra Sen & Apostolos Pesyridis & Andrew Lenton, 2018. "A Scramjet Compression System for Hypersonic Air Transportation Vehicle Combined Cycle Engines," Energies, MDPI, vol. 11(6), pages 1-32, June.
    3. Sasha Veeran & Apostolos Pesyridis & Lionel Ganippa, 2018. "Ramjet Compression System for a Hypersonic Air Transportation Vehicle Combined Cycle Engine," Energies, MDPI, vol. 11(10), pages 1-22, September.
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    Cited by:

    1. Zhang, Tiantian & Wang, Zhenguo & Huang, Wei & Ingham, Derek & Ma, Lin & Porkashanian, Mohamed, 2020. "An analysis tool of the rocket-based combined cycle engine and its application in the two-stage-to-orbit mission," Energy, Elsevier, vol. 193(C).

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