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UID:0-362@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20181024T163000

DTEND;TZID=Asia/Jerusalem:20181024T173000

DTSTAMP:20230527T135651Z

URL:https://aerospace.technion.ac.il/events/miracles-building-and-applying
 -a-high-fidelity-cfd-tool-for-aerospace-engineering-problems/

SUMMARY:MIRACLES: Building and Applying a High-Fidelity CFD Tool for Aerosp
 ace Engineering Problems
DESCRIPTION:Lecturer:Dr. Yann Delorme\n Faculty:Faculty of Mechanical Engin
 eering\n Institute:Technion – Israel Institute of Technology\n Location:
 Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstrac
 t: \n Details: \n Over the past twenty years\, the field of Computational 
 Fluid Dynamics (CFD) has been evolving drastically\, following the progres
 s of computational resources and hardware. The past few years\, Large Eddy
  Simulation (LES) has become more and more popular\, solving for instantan
 eous large scales of the turbulent flow field while modeling the smallest 
 scales\, assumed to be universal. My research focus on the development and
  implementation of high order accurate numerical methods to solve filtered
  Navier-Stokes equations in the context of Large Eddy Simulation. It is ge
 nerally accepted in the community that high order low dissipative numerica
 l methods are needed to accurately capture and predict the large scales of
  turbulent flows. This presents a challenge when trying to simulate realis
 tic complex geometries as high order numerical methods typically benefit f
 rom the use of structured Cartesian meshes.\nIn this seminar\, I will pres
 ent the latest developments of an in-house solver developed at the CFDLab 
 at the Technion (MIRACLES). This solver combines the use of high order ene
 rgy stable numerical methods with an Immersed Boundary Method to allow acc
 urate simulations of complex practical problems. I will go over some detai
 ls of the methods and present several examples related to the aerospace in
 dustry. I will then present how this solver was recently coupled to severa
 l modules to allow for noise prediction of impellers\, and for the computa
 tion of high speed reacting flows in the context of designs of scramjets. 
 Future developments of the solver are finally discussed.
CATEGORIES:Seminars
LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng.

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