Optimization and Application of Busemann Biplane and Its Variants in Supersonic Flight

Abstract

The Busemann biplane is designed to reduce shock wave drag in supersonic flight. With advances in aerospace technology and increasing flight speeds, the potential applications of the Busemann biplane in hypersonic aircraft design have sparked widespread discussion. This paper investigates the aerodynamic characteristics of the Busemann biplane and its variants in supersonic and hypersonic flight, with a focus on the effects of adjusting geometric parameters and relative positioning between the wings on aerodynamic performance. The study demonstrates that the Busemann biplane can effectively reduce drag and improve the lift-to-drag ratio by eliminating shock waves. However, at an angle of attack of 0°, the lift coefficient of the Busemann biplane approaches zero, which poses certain limitations for practical applications. Through experiments analyzing different biplane configurations, it is concluded that increasing the staggered arrangement between the wings further reduces drag and improves the lift-to-drag ratio. This paper highlights the potential of the Busemann biplane in future aircraft design and suggests further optimization of its aerodynamic design to enhance actual flight performance.