Aerodynamic Analysis of a Stagger Supersonic Biplane Airfoil with Leading Edge Flap

The aerodynamic performance of staggered supersonic biplane airfoils equipped with leading-edge flaps is studied using numerical simulation. A parametric analysis is carried out to estimate the effects of the stagger distance and the flap deflection angles on the lift-to-drag ratio, the shock wave interactions, and the overall aerodynamic efficiency. The results show that the optimum stagger configurations significantly reduce the wave drag by up to 18%, while the introduction of leading-edge flaps enhances the lift-to-drag ratio by approximately 22% as compared to the conventional biplane designs without flaps. The optimized flap deflection angles effectively smooth the pressure distributions and delay flow separation, leading to improved aerodynamic stability.