| 摘要 |
The invention is an exhaust nozzle for an after-burning turbojet engine having an exhaust passage mounted in an aircraft, The exhaust nozzle includes a duct having an open first end coupled to the exhaust passage of the turbojet engine, a open second end, and a generally shallow U shape from the first end to the second end. The duct includes top, bottom and side walls, the top and bottom walls converging toward and diverging away from each other along the length of duct from the first to second ends and with the minimum cross-sectional area of the duct or throat positioned down stream of the lowest point of the V. The top wall is pivotally mounted to the aircraft at the first end of the duct so that the throat cross-sectional area can be adjusted to accommodate the increased gas flow when the after-burner is in operation. The bottom wall aft of the throat includes a surface contour for producing a coanda effect.
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