Small-aspect-ratio flying-wing configurations and delta wings exhibit similar aerodynamic characteristics at high angles of attack. Both rely on leading-edge vortices to provide nonlinear lift, and they share common challenges such as sudden shifts in the longitudinal aerodynamic center and nonlinear moment characteristics caused by the unsteady evolution and breakdown of these vortices. Therefore, in the design of such aircraft, particular attention must be paid to the high-angle-of-attack aerodynamic characteristics of both flying-wing vehicles and delta-wing fighters.To improve the accuracy of engineering-practical aerodynamic predictions, this paper introduces an existing rotation/curvature correction into the Shear Stress Transport (SST) turbulence model framework. A numerical study is conducted on the high-angle-of-attack aerodynamic characteristics of both delta wings and small-aspect-ratio flying-wing configurations to systematically evaluate the improvement in predicting leading-edge vortex evolution and aerodynamic forces. By comparing the surface pressure coefficients at different stations of the delta wing and the macroscopic aerodynamic coefficients of the small-aspect-ratio flying-wing configuration with experimental data, it is found that enabling the rotation/curvature correction leads to a decrease in the eddy viscosity coefficient within the leading-edge vortex, an increase in the peak axial velocity of the vortex core, and under transonic flight conditions, an earlier induction of a strong shock wave. This results in an overall attenuation of the negative pressure platform behind the shock and an upstream shift of the vortex breakdown location.Within the Reynolds-Averaged Navier-Stokes (RANS) framework, simply incorporating this existing turbulence model rotation/curvature correction method significantly enhances the prediction accuracy of aerodynamic forces and moments for both delta wings and small-aspect-ratio flying-wing configurations at high angles of attack. This method balances efficiency and accuracy, requiring less grid density and computational cost compared to hybrid turbulence models such as Hybrid Reynolds-Averaged Navier-Stokes/Large Eddy Simulation (Hybrid RANS/LES). It thus provides a fast and low-cost aerodynamic analysis approach for evaluating the takeoff/landing phases and post-stall boundaries of engineering prototypes.