# What is Characteristic Length in a rocket engine?

The characteristic length of a engine's combustion chamber $L^*$ is defined as the ratio of the chamber volume to nozzle throat area:

$$L^*=\frac{V_{chamber}}{A_{throat}}$$

Would it be correct to say that it simply refers to the length of the combustion chamber or, should we say that it is the minimum length over which fuel and oxidizer can undergo stoichiometric combustion?

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