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Abstract Given the escalating demand for hypersonic maneuverability in forthcoming times, it is imperative to advance wide-speed range engine technology, while acknowledging that diverse incoming flow conditions exert a substantial influence on aerothermal processes. The conventional method for calculating aerodynamic performance, which assumes constant specific heat and employs a velocity coefficient parameter, is no longer applicable to aeroengines operating across a wide range of speeds. Therefore, it is crucial to develop an appropriate calculation method for variable specific heat in this type of engine and establish a comprehensive physical property library based on object-oriented programming methodology to cater to the future calculation requirements of diverse engine components. The present study employs polynomial fitting to determine engineering thermodynamic properties, while incorporating the Qin Jiushao (or Horner) algorithm to enhance computational efficiency. The novel approach of utilizing energy conservation and isentropic process principles, in conjunction with numerical methods such as false position, has been employed to ensure the convergence of aerodynamic properties across a wide range of speeds. Subsequently, a novel algorithm is developed for two crucial processes within the intake and exhaust system: the stagnation process and expansion process. Furthermore, a comparative analysis is conducted to discern disparities between these algorithms. Concurrently, employing global sensitivity analysis methodology enables an examination of the impact of altitude and Mach number on the calculated total parameter results. The results indicate that during the stagnation process at 30km, 5Ma, there is an approximate temperature difference of 10% between the two algorithms, while the total pressure difference exceeds 25%. The impact of Mach number on the total temperature is significant, as is the influence of Mach number and altitude on the total pressure. During the expansion process, the critical temperature exhibit minimal difference, but exhaust velocity is dependent on the temperature difference.
Du et al. (Mon,) studied this question.