A power and propulsion system (400, 500, 600, 700), comprising: an air compressor (12, 712, 718); a combustor (14, 724) positioned to receive compressed air from the air compressor as a core stream; and a closed-loop system (404, 504, 722) having carbon dioxide as a working fluid that receives heat from the combustor and rejects heat to a cooling stream, the closed-loop system (404, 504, 722) configured to provide power to a fan (718, 732) that provides the cooling stream, the fan (718, 732) being comprised in the power and propulsion system (400, 500, 600, 700); characterized in that the closed-loop system (404, 504, 722) is further configured to provide power to a plurality of spatially separated distributed propulsors (406, 506, 606, 608) that provide thrust, the plurality of spatially separated distributed propulsors (406, 506, 606, 608) being comprised in the power and propulsion system (400, 500, 600, 700); whereby a distributed propulsion system is obtained; and wherein the closed-loop system (404, 504, 722) includes a first supply manifold (408, 508, 510) and a first return manifold (416, 520, 522), and each of the spatially separated distributed propulsors (406, 506, 606, 608) includes a respective supply line (414, 512, 514) and return line in fluid communication with the respective first supply manifold (408, 508, 510) and first return manifold (416, 520, 522). an air compressor (12, 712, 718); a combustor (14, 724) positioned to receive compressed air from the air compressor as a core stream; and a closed-loop system (404, 504, 722) having carbon dioxide as a working fluid that receives heat from the combustor and rejects heat to a cooling stream, the closed-loop system (404, 504, 722) configured to provide power to a fan (718, 732) that provides the cooling stream, the fan (718, 732) being comprised in the power and propulsion system (400, 500, 600, 700); characterized in that the closed-loop system (404, 504, 722) is further configured to provide power to a plurality of spatially separated distributed propulsors (406, 506, 606, 608) that provide thrust, the plurality of spatially separated distributed propulsors (406, 506, 606, 608) being comprised in the power and propulsion system (400, 500, 600, 700); whereby a distributed propulsion system is obtained; and a fan (718, 732) that provides the cooling stream, the fan (718, 732) being comprised in the power and propulsion system (400, 500, 600, 700); characterized in that the closed-loop system (404, 504, 722) is further configured to provide power to a plurality of spatially separated distributed propulsors (406, 506, 606, 608) that provide thrust, the plurality of spatially separated distributed propulsors (406, 506, 606, 608) being comprised in the power and propulsion system (400, 500, 600, 700); whereby a distributed propulsion system is obtained; and wherein the closed-loop system (404, 504, 722) includes a first supply manifold (408, 508, 510) and a first return manifold (416, 520, 522), and each of the spatially separated distributed propulsors (406, 506, 606, 608) includes a respective supply line (414, 512, 514) and return line in fluid communication with the respective first supply manifold (408, 508, 510) and first return manifold (416, 520, 522).