Flow diagnosis of compressible vortex structures on a 65° delta-wing

With advancements in computational fluid dynamics, high-fidelity simulations enable flow diagnostics of complex flows to identify critical local structures affecting aerodynamic performance. Based on compressible vortex-force theory, the generalized Lamb vector’s spatial distribution elucidates force generation mechanisms. This study employs the shear stress transport k - ω turbulence model within the Reynolds-averaged Navier-Stokes equations to accurately capture viscous-dominated boundary layers and shock-induced separation phenomena. Additionally, an aerodynamic computed topography is also utilized to quantify lift contrasting subsonic ( Ma ∞ = 0.4) and supersonic ( Ma ∞ = 2.0) flows: incompressible Lamb vector contributions dominate subsonic regimes, while compressibility effects characterized by the compressibility term, k ∇ ρ , prevail in supersonic regimes. The spanwise and freestream-direction components of the Lamb vector and compressibility term are quantitatively evaluated for lift. For delta wings at high angles of attack, zonal scanning decouples vortex-force contributions from separated flow regions, revealing key flow structures governing lift. The vortex-force diagnosis sheds new light on the flow control and configuration optimization.