International Journal of Aerospace Engineering / 2008 / Article / Fig 2

Research Article

Transient Burning Rate Model for Solid Rocket Motor Internal Ballistic Simulations

Figure 2

Predicted unsteady head-end pressure-time profile, for SRM undergoing axial combustion instability symptoms ( 𝐾 𝑏 = 2 0 0 0 0  s−1, Δ 𝐻 𝑠 = 1 5 0 0 0 0  J/kg, Δ 𝑝 𝑑 = 2  atm).
26070.fig.002

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