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SUMMARY:Shock control on transonic wings by three-dimensional bumps. - Sim
 on Collis\, CUED 
DTSTART:20130510T120000Z
DTEND:20130510T131500Z
UID:TALK44738@talks.cam.ac.uk
CONTACT:ROBERTA TRUPIANO
DESCRIPTION: The aerodynamics of modern transport aircraft wings are chara
 cterised by the appearance of weak normal (or near-normal) shock waves\, w
 hich lead to an additional drag component (wave drag) and the possibility 
 of buffet - oscillatory shock motion caused by the interaction of regions 
 of shock-induced and trailing-edge boundary layer separation.  Both of the
 se phenomena effectively limit the operational speed of the aircraft\, and
  controlling them is therefore desirable.  One method that has shown consi
 derable promise is the ‘shock control bump’ (SCB).  Although there hav
 e been extensive studies on SCB performance conducted in previous years\, 
 the details of the flow physics still require research to enable improved 
 designs that are more robust to off-design conditions.  The present work e
 xamines flow features of shock bumps through a combination of experimental
  and computational investigations\, highlighting the connection between bu
 mp geometry and flow properties.  The SCB is also shown to produce streamw
 ise vortices capable of exerting a degree of direct boundary layer control
 \, and the origin of this flow feature is investigated.  This suggests the
  potential of the SCB of acting as a new class of ‘smart’ vortex gener
 ator that offsets the viscous penalty of vortex generation by reduction of
  other shock-related drag components. 
LOCATION:LR10\, Baker Building (South wing).
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