A computational study that aimed to predict the heat transfer (HT) and ablation rates for carbon/carbon composite, epoxy resin, and hydrated magnesium sulphate (HMS) in a hypersonic environment is presented. The motivation for this work lies in the importance of accurate modelling for designing and improving the performance of hypersonic vehicles. The high temperatures and pressures experienced during hypersonic flight can cause severe thermal stresses on the vehicle, leading to material degradation and failure. Therefore, accurate prediction of heat transfer and ablation rates is essential for ensuring the safety and performance of these vehicles. Towards this end, we have developed and validated a fluid-thermal-ablation coupling model that can accurately predict the heat transfer and ablation rates in a hypersonic environment. The study demonstrates that the model can be used to improve the design and performance of hypersonic vehicles by providing accurate predictions of thermal stresses on the vehicle. The study also highlighted the importance of accurate modelling for ensuring the safety and performance of hypersonic vehicles.