Numerical analysis of stagger Supersonic biplane at off-design condition with trailing edge flap

Supersonic biplanes can achieve low-boom and low-drag supersonic flights. In the present study, aerodynamic analysis of a two-dimensional stagger Bussmann biplane (staggered upper element by 0.5c) at zero degrees angle attack with trailing edge flap was investigated help computational fluid dynamics (CFD) tools. Due to wave cancellation effect, Busemann delivers positive drag reduction design Mach values. However, when operating outside its intended parameters, it performs worse, effect has no beneficial effects on reducing drag. Another issue is flow chocking, which produces potent bow shock in front aircraft. This paper attempts address low aerodynamics efficiency problems during take-off through numerical simulation staggered flaps attack. It confirmed that airfoil better performance lower subsonic free stream numbers. 2D wings, chocking hysteresis as starting problems, arise accelerate from numbers, reduced using suitable dimension rotation flap, effective settling these issues.