A variable cycle propulsion 
system for a supersonic 
airplane, the 
system comprising at least one engine having means for producing 
exhaust gas and a gas exhaust 
nozzle for generating thrust for supersonic flight speeds, and at least one separate auxiliary propulsion 
assembly dissociated from said engine, having no 
gas generator, and capable of generating thrust for 
takeoff, landing, and subsonic flight speeds. The 
system further comprises gas flow tapping means movable between a position in which they tap off at least a fraction of the 
exhaust gas produced by said engine and feed it to said propulsion 
assembly to enable it to generate thrust for 
takeoff, landing, and subsonic cruising flight, and a position in which the gas produced by the engine is directed solely to the engine 
nozzle for supersonic cruising flight.