This page provides the Rocket Motor Design Module user with a visual definition of Nozzle Geometry for the Rocket Motor Simulation Module.

The figure below shows a picture of the key geometry of the Rocket Motor Nozzle.

The Nozzle Throat Diameter is the diameter of the narrowest portion of the exhaust nozzle.

The Nozzle Exit Half Angle is the angle between the centerline of nozzle longitudinal axis and the wall of the nozzle.

The Cant of Nozzles is the angle between the nozzle centerline and the longitudinal axis of the rocket motor grain. It is not shown in this figure.

The Nozzle Area Ratio is the ratio of the area of the nozzle exhaust to the area of nozzle throat.

The Nozzle Exit Diameter is the diameter of the nozzle where the exhaust gas is no longer confined by nozzle structure.

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