Aerodynamic Characteristics Analysis of Transonic Wing Flow Around Space Shuttle

The Space Shuttle orbiter, a pioneering reusable spacecraft, navigated complex aerodynamic challenges during atmospheric re-entry. This paper investigates the aerodynamic behavior of transonic flow around its delta-wing design, focusing on shock-induced separation, vortex formation, and unsteady aerodynamic effects during descent and landing phases. Utilizing computational fluid dynamics (CFD) methods, including Euler and NavierStokes equations with zonal grid techniques, alongside experimental wind-tunnel campaigns, the study evaluates lift, drag, pressure distribution, and stability derivatives across Mach numbers from 0.8 to 1.2. Key findings highlight the significant influence of wingbody aerodynamic coupling on flutter speed and control surface effectiveness. By integrating numerical predictions with empirical data, the analysis validates existing models and provides insights into practical implications for future aerospace vehicle design. The results offer engineers critical guidance for optimizing designs and mitigating aeroelastic risks, particularly in reentry and subsonic-to-transonic transition scenarios.