Mach Number Effect on Flowfield Over a Delta Wing in Supersonic Region

Computational investigation of vortex structure and breakdown over a delta wing at supersonic pitching maneuver

“…Therefore, only half of the wing is covered by the computational domain. Flow asymmetry over delta wings in the angle of attack range [19] studied in this paper, with the absence of yaw angle, has little effect on flow pattern and aerodynamic characteristics, while it halves the computational cost, so that it has been used in previous computational works [26][27][28][29]. The simulations were performed on an unstructured grid ( Fig.…”

“…Imai et al [25] conducted computational simulations of flow field over a 65°sweep delta wing and investigated the flow mechanism behind the flow classification at high angles of attack in transonic and supersonic regimes. Oyama et al [26] performed wind tunnel experiments to examine the effect of Mach number on flow structure over a delta wing with blunt leading edges in supersonic and high angle of attack regions.…”

Computational Investigation of Vortex Breakdown over a Pitching Delta Wing at Supersonic Speeds

“…Imai et al [19] conducted computational simulations of ow eld over a 65 sweep delta wing and investigated the ow mechanism behind the ow classi cation at high angles of attack in transonic and supersonic regimes. Oyama et al [20] performed wind tunnel experiments to examine the e ect of Mach number on ow structure over a delta wing with blunt leading edges in supersonic and high angle of attack regions.…”