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SUMMARY:Shock-induced boundary-layer separation in transonic intakes at of
 f-design climb - Connor O'Pray\, Oxford
DTSTART:20260318T140000Z
DTEND:20260318T150000Z
UID:TALK243919@talks.cam.ac.uk
CONTACT:Anna Walczyk
DESCRIPTION:The gas-turbine nacelle accounts for 10% of civil aircraft dra
 g\, which could be minimised by reducing nacelle size. However\, reducing 
 nacelle diameter often worsens engine performance at off-design conditions
 \, creating a trade-off between operability and drag reduction. During off
 -design climb\, a transonic shock wave–boundary-layer interaction (SBLI)
  tends to form on the windward intake surface (inner nacelle surface). A s
 hock-induced boundary-layer separation may cause a loss of thrust and stab
 ility margin. Could an improved understanding of how intake surface shape 
 influences SBLI behaviour enable smaller nacelles without this compromise 
 in engine performance? A quasi-two-dimensional experimental study was cond
 ucted under representative off-design climb conditions. Three geometric pa
 rameters of the intake surface were varied across three operating points t
 o provide 27 test-cases in a Design of Experiments structure. This work pr
 esents: (i) a novel characterisation of the relationship between an SBLI a
 nd intake performance\, (ii) a recommended limit for shock strength to avo
 id significant performance reduction\, and (iii) recommendations on the op
 timal shaping of the windward intake surface to enable smaller\, lower-dra
 g nacelles.
LOCATION:LT5
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