Propulsion aerodynamics for a novel high-speed exhaust system

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dc.contributor.authorTsentis, Spyros
dc.contributor.authorGoulos, Ioannis
dc.contributor.authorPrince, Simon
dc.contributor.authorPachidis, Vassilios
dc.contributor.authorZmijanovic, Vladeta
dc.date.accessioned2023-10-04T12:24:53Z
dc.date.available2023-10-04T12:24:53Z
dc.date.issued2023-09-28
dc.description.abstractA key requirement to achieve sustainable high-speed flight and efficiency improvements in space access, lies in the advanced performance of future propulsive architectures. Such concepts often feature high-speed nozzles, similar to rocket engines, but employ different configurations tailored to their mission. Additionally, they exhibit complex interaction phenomena between high-speed and separated flow regions at the base, which are yet not well understood, but are critical in terms of pressure and viscous forces. This paper presents a numerical investigation on the aerodynamic performance of a representative novel exhaust system, which employs a high-speed, truncated, ideal contoured nozzle and a complex-shaped cavity region at the base. Reynolds-Averaged Navier-Stokes computations are performed for a number of Nozzle Pressure Ratios (NPRs) and free stream Mach numbers in the range of 2.7 < NPR < 24 and 0.7 < M∞ < 1.2 respectively. The corresponding Reynolds number lies within the range of 1.06 · 106 < Red < 1.28 · 106 based on the maximum diameter of the configuration. A decomposition of the drag domain forces exposes the major trends between the constituent elements. The impact of the cavity on the aerodynamic characteristics of the apparatus is revealed by direct comparison to an identical non-cavity configuration. Results show a consistent trend of increasing base drag with increasing NPR for all examined M∞ for both configurations. This is attributed to the jet entrainment effect and to the lower base pressure imposed by the higher jet flow expansion. The cavity region is found to have almost no impact on the incipient separation location of the nozzle flow. At low supersonic speeds of M∞ = 1.2 and high NPRs, the cavity has a significant effect on the aerodynamic performance, transitioning nozzle operation to under-expanded conditions. This results in approximately 12% higher drag coefficient compared to the non-cavity case and shifts the minimum NPR for which the system produces positive gross propulsive force to higher values.en_UK
dc.description.sponsorshipReaction Engines Ltd. Cranfield Air and Space Propulsion Institute (CASPI)en_UK
dc.identifier.citationTsentis S, Goulos I, Prince S, et al., (2023) Propulsion aerodynamics for a novel high-speed exhaust system. In: ASME Turbo Expo 2023: Turbomachinery Technical Conference and Exposition, 26-30 June 2023, Boston, MA, Paper Number GT2023-101005en_UK
dc.identifier.isbn978-0-7918-8693-9
dc.identifier.urihttps://doi.org/10.1115/GT2023-101005
dc.identifier.urihttps://asmedigitalcollection.asme.org/GT/proceedings-abstract/GT2023/86939/V001T01A010/1167744
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/20327
dc.language.isoenen_UK
dc.publisherAmerican Society of Mechanical Engineers (ASME)en_UK
dc.rightsAttribution 4.0 International*
dc.rights.urihttp://creativecommons.org/licenses/by/4.0/*
dc.subjectaerodynamicsen_UK
dc.subjectexhaust systemsen_UK
dc.subjectthrust and drag accountingen_UK
dc.subjectTIC nozzleen_UK
dc.subjectbase cavityen_UK
dc.subjectbase dragen_UK
dc.titlePropulsion aerodynamics for a novel high-speed exhaust systemen_UK
dc.typeConference paperen_UK

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