= Rocket fuel fraction
{title2=$f=m_{\mathrm{fuel}}/m_0$}
In an ideal <rocket equation> calculation where all expelled <rocket propellant> is called fuel, the <rocket fuel fraction> is its initial <mass> divided by the total initial <mass>, including payload and structure. Complete consumption leaves <rocket dry mass> $m_f=(1-f)m_0$ and <rocket mass ratio> $m_0/m_f=1/(1-f)$. The payload is one component of $m_f$, not an additional <mass> to add to an already inclusive $m_0$.
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