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Engine sizing involves a large number of variables both quantitative and qualitative. However, nearly all of these can be contained constrained by the selection of a propellant combination and two of the following three variables: chamber pressure (

Eazy math inline
bodyP_{c}
), thrust (
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bodyF_{t}
), and mass flow rate (
Eazy math inline
body\dot{m}
). Selecting two of these and a propellant combination will allow you to proceed to NASA CEA and define engine performance and size.

See the following pages for more details on: Selecting Propellant Combination , Selecting a Design Thrust, and Selecting a Preliminary Chamber Pressure.

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