Abstract: The effective and efficient thermal protection is one of the main bottlenecks restraining the development of hypersonic vehicles. The existing thermal protection technologies, for example, those with the use of advanced ceramic matrix composite or ablative materials, cannot fully meet the thermal protection requirements in the extreme thermal environment. Thus, the active jet thermal protection based on air film cooling is adopted to reduce the heat flux and the temperature of the hypersonic vehicle head. The thermal environment of this structure with different jet cooling solutions is studied via numerical analysis. It is shown that under the single-hole jetting condition with the same injecting velocity, the larger the hole diameter is, the lower the heat flux peak would be at a price of the flow rate; and with the commensurate expanding hole, one sees a smaller heat flux than with the straight hole at a similar jet flow rate. From a comparison with the same cooling effect, the multi-hole jet seems a better choice as it can reduce the heat flux by 50%.