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Engine sizing involves a large number of variables both quantitative and qualitative. However, nearly all of these can be constrained by the selection of a propellant combination and two of the following three variables: chamber pressure (
), thrust (
), and mass flow rate (
). Selecting two of these and a propellant combination will allow you to proceed to NASA CEA and define engine performance and size. Oftentimes
, these parameters are driven by systems-level requirements such as certain vehicle performance/flight profile requirements, propellant selection dictated by a challenge/competition/school rules, or any number of program requirements.
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