International Journal of Aerospace Engineering / 2008 / Article / Tab 1

Research Article

Transient Burning Rate Model for Solid Rocket Motor Internal Ballistic Simulations

Table 1

Propellant characteristics.


𝜌 𝑠 (J/kg-K)15001500130015001675
π‘˜ 𝑠 (kg/m3)17301730158017301620
𝛼 𝑠 (W/m-K)
𝑇 𝑠 (m2/s)1.54 Γ— 10βˆ’71.54 Γ— 10βˆ’78.28 Γ— 10βˆ’81.54 Γ— 10βˆ’71.47 Γ— 10βˆ’7
𝑇 𝑖 (K)100010007501000650
𝑛 (K)294294294294300
𝐾 𝑏 0.350.460.450.650.69

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