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SUMMARY:Sidewall effects in compression corner shock wave boundary layer i
 nteractions - Rhys Williams (University of Cambridge)
DTSTART:20230303T124500Z
DTEND:20230303T134500Z
UID:TALK195151@talks.cam.ac.uk
CONTACT:Paras Vadher
DESCRIPTION:If we wish to design a commercial aircraft to fly faster than 
 sound we are faced with the problem of decelerating the incoming supersoni
 c flow to a subsonic flow that our engine turbomachinery can handle. We ar
 e forced to achieve this using shock waves. These shock waves will impinge
  on the boundary layers forming on the walls of our inlet\, and as a resul
 t\, complex shock wave boundary layer interactions (SBLIs) will occur. The
 se SBLIs can separate the flows in our inlets with consequences ranging fr
 om drops in engine efficiency to catastrophic unstart of the inlet. We lac
 k a good understanding of what can influence the scale of separations in t
 hese interactions. In this talk we will take the ideally two-dimensional e
 xample of the compression corner SBLI\, and examine though wind tunnel exp
 eriments how real world geometries\, taking the example of rectangular cro
 ss sectioned ducts\, can induce complex three dimensional effects\, and we
  will seek to find explanations for these so called ‘sidewall effects’
 . \n\n
LOCATION:LR5
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