International Journal of Aerospace Engineering

Research Article

Transient Burning Rate Model for Solid Rocket Motor Internal Ballistic Simulations

Table 1

Propellant characteristics.
Propellants
ABCDE
𝜌 𝑠 (J/kg-K)15001500130015001675
𝑘 𝑠 (kg/m3)17301730158017301620
𝛼 𝑠 (W/m-K)0.40.40.170.40.4
𝑇 𝑠 (m2/s)1.54 × 10−71.54 × 10−78.28 × 10−81.54 × 10−71.47 × 10−7
𝑇 𝑖 (K)100010007501000650
𝑛 (K)294294294294300
𝐾 𝑏 0.350.460.450.650.69