Propelling nozzle for a hypersonic jet plane

A single common propelling nozzle having a nozzle flow in a downstream direction for a combined turboramjet engine, comprising:

• a rectangular nozzle housing having parallel wall surfaces;
• upper primary and secondary flaps;
• lower primary and secondary flaps, both said upper and lower primary and secondary flaps forming a nozzle contour of said common nozzle having a variable course for both gas turbojet and ramjet engine operation and a variable narrowest cross-section;
• said primary flaps being pivotally connected upstream from said nozzle housing and having secondary flap pivots located on the side of said primary flaps facing away from the nozzle flow, said variable narrowest cross-section being located between pivot facing sides of said upper and lower secondary flaps;
• said secondary flaps being pivotally connected to said secondary flap pivots;
• wherein the gas turbojet and ramjet engines are axially arranged above one another and each have an outlet duct ending in said common nozzle at said variable narrowest cross-section, further comprising:
• a partition having top and bottom sides and a downstream end section, provided between both outlet ducts extending in the downstream direction to a narrowest cross-section of the single propelling nozzle;
• means for placing said primary and secondary flaps in positions providing an aerodynamically advantageous nozzle flow on both sides of said partition in a transition area of the primary to secondary flaps.