| | Parameter | Value |
| | Geometry | | | Length of combustion chamber, | 13.55 mm | | Camber diameter, | 9 mm | | Length of barrel, | 150 mm | | Barrel diameter (caliber), | 9 mm | | Physical properties | | | Projectile mass, | 8.00 g | | Propellant mass, | 0.245 g | | Initial propellant particle diameter, | 0.300 mm | | Propellant density, | 600 kg/m3 | | Propellant heat of combustion, | 1.135 MJ/kg | | Specific heat of propellant, | 120.32 | | Thermal conductivity of propellant, | 0.0164 W/m/K | | Specific heat of gas at constant pressure, | 1858 J/kg/K | | Specific heat ratio of gas, | 1.24 | | Viscosity of gas products, | 0.134064 (/298)1.5/( + 110) kg/m/s. [7] | | Conductivity of gas products, | 0.05225 (/700)0.7 J/s/m/K. [27] | | Constitutive laws | | | Coefficient in burning law, | 2.0 × 10−9 m/s/ | | Exponent in burning law, | 1.02 | | Coefficient in burning law, | 0 | | Engraving pressure, | 40 MPa | | Numerical data | | | Number of initial cells, | 70 | | Time step, | 10−07−10−09 s |
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