To investigate the vortex breakdown over the ONERA70 delta wing at an angle-of-attack of 27°, unsteady simulations were performedusing Reynolds-averaged Navier-Stokes and Spalart-Allmaras delayed detached-eddy simulations. A low-diffusive preconditioned Roescheme with third-order MUSCL interpolation scheme was applied, along with second-order dual-time stepping combined with diagonalizedalternating direction implicit method for unsteady simulation. Vortex breakdown was investigated through an examination oftotal pressure loss, axial velocity, and axial vorticity around the primary vortex. Delayed dtached-eddy simulation provided good agreementwith experimental data and predicted all physical phenomena related to vortex breakdown well.
Computational fluid dynamics; Delta wing; Dlayed detached-eddy simulation(DDES); High angle of attack; Reynolds-averaged Navier-Stokes (RANS); Vortex breakdown