Numerical Navier-Stokes equation solutions involve complicated fluid flow models, requiring advanced computational methods. The Lattice Boltzmann Method (LBM) is a reliable fluid dynamics simulation method for complicated geometries, nonlinear boundary conditions, and unsteady flows. LBM evolves particle distribution functions on a discrete lattice instead of solving the Navier-Stokes equations at the macroscopic level. It accurately simulates macroscopic fluid equations and has simplified boundary condition implementation, compatibility with complicated domain topologies, and greater scalability for parallel computing on high-performance platforms. This study uses the LBM with the D3Q27 model to examine the X-wing UAV’s aerodynamic performance, focusing on wing interactions and ground effects. Simulations show that the NACA 4412 airfoil excels in lift (2.5–3.0; lift-to-drag ratio up to 60) at low altitudes (0.12–0.2 m) and angles of attack (5 \(^\circ \) and 10 \(^\circ \) ), making it ideal for high-lift missions. Conversely, the Clark Y airfoil exhibits greater stability (lift-to-drag ratio of 20–30) at angles of 0 \(^\circ \) –5 \(^\circ \) with minimal height sensitivity, suitable for precision tasks. Both airfoils experience performance degradation beyond a 15 \(^\circ \) angle of attack due to flow separation. Although LBM is well-established, this study is the first to compare NACA 4412 and Clark Y air-foils on a complicated X-wing UAV configuration, measuring low-altitude ground effect performance trade-offs.