Shock-induced fan cowl separation during aeroengine windmilling at diversion from cruise

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dc.contributor.authorSabnis, Kshitij
dc.contributor.authorBabinsky, Holger
dc.contributor.authorBoscagli, Luca
dc.contributor.authorMacManus, David
dc.contributor.authorSheaf, Christopher
dc.date.accessioned2024-11-18T12:45:28Z
dc.date.available2024-11-18T12:45:28Z
dc.date.freetoread2024-11-18
dc.date.issued2024-11-13
dc.date.pubOnline2024-11-13
dc.description.abstractWhen a civil aircraft engine is operated at windmill during the cruise flight phase, there is supersonic flow acceleration around the leading edge of the fan cowl toward the external surface. The terminating normal shock wave can separate the turbulent boundary layer developing on this external surface. A series of experiments at a flight-relevant Reynolds number (1.2 million based on lip thickness) are performed in a quasi-two-dimensional wind tunnel rig to investigate the underlying flow physics. At a nominal inflow Mach number of 0.65 and a nacelle incidence angle of 4.5 deg, as the equivalent engine mass-flow rate is reduced, an increase in shock strength results in flow separation when the shock exceeds Mach 1.4. Over a 10% range in the notional engine mass-flow rate, the boundary layer developing on the external fan cowl thickens by a factor of three on the onset of separation. A reduction in the incoming Mach number from 0.65 to 0.60 weakens the shock wave and thus delays separation. An increase in surface roughness has no significant effect in situations where the boundary layer remains attached. However, for separated cases, an increased local roughness height causes a greater separation extent and a thicker boundary layer downstream of the shock wave.
dc.description.journalNameAIAA Journal
dc.description.sponsorshipThis project has received funding from the Clean Sky 2 Joint Undertaking (JU) under Grant Agreement No. 101007598. The JU receives support from the European Union’s Horizon 2020 research and innovation program and the Clean Sky 2 JU members other than the union.
dc.identifier.citationSabnis K, Babinsky H, Boscagli L, et al., (2024) Shock-induced fan cowl separation during aeroengine windmilling at diversion from cruise. AIAA Journal, Available online 13 November 2024
dc.identifier.eissn1533-385X
dc.identifier.elementsID558748
dc.identifier.issn0001-1452
dc.identifier.urihttps://doi.org/10.2514/1.j064521
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/23200
dc.languageEnglish
dc.language.isoen
dc.publisherAmerican Institute of Aeronautics and Astronautics (AIAA)
dc.publisher.urihttps://arc.aiaa.org/doi/10.2514/1.J064521
dc.rightsAttribution 4.0 Internationalen
dc.rights.urihttp://creativecommons.org/licenses/by/4.0/
dc.subjectAerospace & Aeronautics
dc.subject4001 Aerospace engineering
dc.subject4012 Fluid mechanics and thermal engineering
dc.subjectAircraft Engines
dc.subjectBoundary Layer Separation
dc.subjectFreestream Mach Number
dc.subjectAircraft Components and Structure
dc.subjectShock Waves
dc.subjectTransonic Wind Tunnel
dc.subjectSeparated Flows
dc.subjectTerminating Normal Shock
dc.subjectNacelles
dc.titleShock-induced fan cowl separation during aeroengine windmilling at diversion from cruise
dc.typeArticle
dcterms.dateAccepted2024-09-10

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