Coupled flow-thermal analysis is crucial for the performance evaluation and structural design of hypersonic vehicles. In this study, several strategies for computing the coupled fl ow-thermal response of air-breathing hypersonic fl ights in practical engineering are developed and compared. First, the basic direct correction method that amends wall heat fl ux via recovery temperature and wall temperature is proposed to approximate fl ow-thermal eff ects effi ciently. Second, the improved DCM (IDCM) is further developed by interpolating the cold wall heat fl ux and the recovery temperature between adjacent trajec�tory points to improve computational accuracy. Third, the iteration solution method (ISM) that obtains solutions through mass and energy balances at a common interface by iterations between CFD analysis code and CSD analysis code is also presented. Thermal response and fl ow characteristics are compared through a test case of an air-breathing hypersonic vehicle. The results show that the thermal response tendencies are consistent by DCMs and ISM. However, for DCMs, the impact of hot wall on the fl ow characteristics is ignored, whereas it is fully considered in ISM; thus, the thickened boundary fl ow and complicated internal fl ow can be captured. However, while comparing computational effi ciency, DCMs have a prominent advantage over ISM due to the decoupling algorithm and parallel strategy. Based on this, in the actual design process of an air-breathing hypersonic vehicle, the designers can select the proper fl ow-thermal analysis method according to the diff erent design stages.