Abstract: In order to quickly evaluate the applicability of different types of engine schemes for reusable wide-range high-speed aircraft, those engine schemes in the low-speed phase which is the most critical part for the feasibility evaluation, are reviewed. The difference in basic principles between different propulsion schemes for solving the wide-range work problems is systematically studied. The working process and performance of each scheme are given, and the target aircraft adapted to the typical scheme is summarized and analyzed to support the engine scheme design. The research results show that different mission requirements of the wide-range high-speed aircraft have important impacts on the selection of low-speed-phase engine schemes, especially between the wide-range acceleration mission and the high-speed cruise mission. However, as the upper limit of the aircraft's Mach number increases, the difference in the selection of propulsion schemes in the low-speed phase between the two missions is narrowed. For a wide-range high-speed aircraft with a certain flight mission, the low-speed power scheme that can meet its requirement is not unique. The variable cycle engine scheme based on turbofans, the fuel precooling engine scheme, and the combined RBCC and turbofan scheme are all applicable to the acceleration mission as well as the high Mach number cruise mission. The low-speed engine schemes based on the modification and combination of existing engines have a good application prospect in the first stage of the two-stage-to-orbit (TSTO) vehicle with low cost and high agility.