Numerical Analysis of Vortex-Vortex and Vortex-Shock Interactions at Hybrid-Delta-Wing Configurations

This study examines the vortex-dominated flow field around triple-delta and double-delta-wing configurations under transonic flow conditions, with an emphasis on vortex-vortex and vortex-shock interactions. In this regard, numerical simulations were conducted at Mach numbers of 0.75, 0.85, and 0.95 for an angle of attack range of 16° ≤ α ≤ 32°. Validation against the experimental data reveals that scale-resolving simulations provide improved accuracy, particularly at high incidence angles. Inboard vortex breakdown occurs further downstream with increasing Mach number at α = 16°. At a Mach number of 0.85, two normal shocks form on the triple-delta wing, whereas a single shock forms on the double-delta wing at α = 16°. The inboard vortex of the triple-delta wing undergoes breakdown upon interacting with the second shock at α = 16°, while it bursts upstream of the shock at α = 24°. In contrast, a more robust inboard vortex develops on the double-delta wing, and it does not burst at α = 16° and α = 24° on the wing despite the shock. Finally, sideslip conditions result in a more intense vortex system on the windward side, bursting abruptly and causing asymmetric lift generation at α = 24°. This roll reversal is captured in the numerical results for both configurations.