Which process limits the maximum sustained burn rate in solid rocket boosters with fuel-rich propellants?

💡 Explanation

When fuel-rich propellants are used, the diffusion rate of oxidizer towards the flame front becomes the limiting factor because complete combustion cannot occur without sufficient oxidizer supply, slowing energy release. Therefore the diffusion rate limits burn rate, rather than heat transfer, nozzle erosion, or casing stress, which depend different rocket designs.

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