With the development of hypersonic aircrafts, the temperature and pressure of combustor would significantly increase for high-performance engines in the future, and the supercritical condition will gradually appear in the engine combustor. As the combustor environment reaches to a supercritical condition, the critical phase transition, high-gradient heat and mass transfer will appear, thus leading to different processes of fuel injection, evaporation and combustion from ones under the normal condition. Therefore, an overall related research review about fuel droplet evaporation and combustion in a supercritical environment is provided in this study. Significant results to date are summarized and challenges for subsequent study are clarified, which may be helpful to the further exploration in this area.