Cumulative thermal deformation occurs under the long periods of aerodynamic/thermal coupling when an aircraft flies at High-speed. The adverse effects of this deformation on aerodynamic performance throughout the flight have become a critical challenge in the design and development of next-generation aircraft. In this study, a real complex wing structure is investigated. Using a self-developed thermal environment-thermal response coupling analysis platform (NNW-CAPTER) and a high-speed flow simulation software platform (NNW-HyFLOW), a one-way coupling strategy accounting for temperature rise effects is adopted to analyze the evolution law of cumulative thermal deformation under varying Mach numbers and angles of attack. Results indicate that the cumulative thermal deformation of the wing structure requires thousands of seconds to stabilize. Mach number significantly influences the deformation magnitude and temperature rise rate, while the angle of attack primarily affects the time required for deformation and temperature stabilization. These deformation patterns alter the wing’s aerodynamic characteristics, causing the decrease of lift/drag coefficients and pitch moment coefficients. These detrimental impacts intensify in correlation with the escalation of the Mach number and the angle of attack, with the negative repercussions on aerodynamic characteristics progressively amplifying. It is imperative that such issues are proactively tackled during the aircraft design.