Authors: Mi So Son Jeong Hwan Sa Soo Hyung Park Yung Hwan Byun Kum Won Cho
Publish Date: 2015/08/09
Volume: 29, Issue: 8, Pages: 3205-3213
Abstract
To investigate the vortex breakdown over the ONERA70 delta wing at an angleofattack of 27° unsteady simulations were performed using Reynoldsaveraged NavierStokes and SpalartAllmaras delayed detachededdy simulations A lowdiffusive preconditioned Roe scheme with thirdorder MUSCL interpolation scheme was applied along with secondorder dualtime stepping combined with diagonalized alternating direction implicit method for unsteady simulation Vortex breakdown was investigated through an examination of total pressure loss axial velocity and axial vorticity around the primary vortex Delayed dtachededdy simulation provided good agreement with experimental data and predicted all physical phenomena related to vortex breakdown wellSoo Hyung Park is a Professor at the Department of Aerospace Information Engineering Konkuk University Korea His research interests include CFD based on the structured mesh technique turbulence modeling rotorcraft aerodynamics and largescale supercomputing
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