A rapid steady/unsteady aerodynamic analysis method based on panel method coupled boundary layer theory

While high-fidelity computational fluid dynamics (CFD) demonstrates exceptional analytical capabilities, it is crucial to develop aerodynamic analysis methodologies that balance computational efficiency with high fidelity, especially in aircraft design during conceptual phases and multidisciplinary optimization scenarios. This study develops a two-dimensional unsteady differential boundary layer equation solver and integrates it into an unsteady three-dimensional panel method framework. The flow domain is partitioned into viscous and inviscid potential flow regions, with boundary layer equations and panel method solutions computed separately. A bidirectional coupling mechanism is established: displacement thickness derived from viscous boundary layer solutions modifies panel method boundary conditions, while surface velocities from the panel method serve as input for boundary layer computations. Validation using wind tunnel data for the Eppler 387 airfoil and CFD simulations for the NACA0012 airfoil confirms the solver's accuracy and applicability. Subsequent analysis of unsteady aerodynamic characteristics for a harmonically oscillating high-aspect-ratio wing reveals that the three-dimensional panel method with boundary layer viscous correction achieves significant accuracy improvements over conventional three-dimensional panel methods, with computational duration per oscillation cycle reduced to 1% of CFD requirements.