Effect of sweep angle on the vortical flow over delta wings at an angle of attack of 10°

Cfd simulations have been used to analyse the vortical flows over sharp edged delta wings with differing sweep angles under subsonic conditions at an angle of attack of 10°. rans simulations were validated against experimental data for a 65° sweep wing,with a flat cross-section,and the steadiness of the flow field was assessed by comparing the results against unsteady urans and des simulations. to assess the effect of sweep angle on the flow field,a range of sweep angles from 65° to 43° were simulated. for moderate sweep wings the primary vortex was observed to detach from the leading edge,undergoing vortex breakdown,and a weaker,replacement,“shadow” vortex was formed. the shadow vortex was observed for sweep angles of 50° and less,and resulted in reduced lift production near the wing tips loss of the stronger primary vortex. © school of engineering,taylor’s university.