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  1. The propellant combination is one of the most significant factors in engine sizing. Nitrous Oxide, N2O is our oxidizer, and Isopropyl Alcohol, IPA is our fuel. IPA was selected as fuel due to its low cost and accessibility.

  2. Engine sizing is constrained by three main variables, chamber pressure

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    body(P_{c})
    , thrust
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    body(F_{t})
    , and mass flow rate
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    body(\dot{m})
    . We used a Simulink simulation to decide on an
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    bodyF_{t}
    of
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    body2500N
    and metallurgy and COTS valve/fitting pressure contracts to arrive at a
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    body(P_{c})
    of
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    body2500kPa
    /
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    body362.6Psi
    .

  3. Using NASA CEA. We input

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    bodyP_{c}
    ,
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    bodyP_{e}
    , and a number of mass fractions for our N2O oxidizer and IPA fuel. CEA outputs
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    body\frac {A_{e}} {A_{t}}
    ,