Cathode ejector cooling flow control system

A fuel cell powered airplane, comprising integrated hydrogen-electric engine including:

• a hydrogen fuel cell;
• an air inlet coupled to a cooling duct integrated into the aircraft, and
• a cooling system having a heat exchanger radiator in the cooling duct, and configured to direct an air stream comprising an air stream from the air inlet through the radiator, and wherein an exhaust stream from a cathode side of the fuel cell is fed into the cooling duct, wherein the cathode exhaust stream is fed via a flow control nozzle into the air stream in the cooling duct both upstream and downstream of the heat exchanger radiator, wherein the cathode exhaust feed into the air stream in the cooling duct downstream of the heat exchange radiator is introduced through a porous wall of the cooling duct.