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An investigation was conducted to determine the effects on internal performance of several geometric variables that were intended to produce a short, high-performance convergent-divergent nozzle. It was found that shortening the convergent section by either changing its shape or decreasing the throat-contour radius had no effect on thrust coefficient. It was also found that a nozzle with a short conical divergent section had a higher thrust coefficient than a nozzle with either a stepped or contoured divergent section of approximately equal length.