Name*

Country of Origin

--------- Austria-Hungary France Germany Italy Japan Russia/USSR United States United Kingdom other not set

Specific Heat Ratio*

dimensionless

Specific Force*

kJ/kgcal/lbcal/gft·lbf/lbin·lbf/lb

Flame Temperature*

°K°R°C°F

Co-volume*

mm³/kgin³/lbmm³/gcm³/gm³/kg

Density*

kg/mm³g/cm³lb/in³kg/m³

Burn Rate Coefficient*

m·s⁻¹·MPa⁻¹in·s⁻¹·psi⁻¹in·s⁻¹·kpsi⁻¹mm·s⁻¹·Pa⁻¹m·s⁻¹·Pa⁻¹

Burn Rate Exponent*

dimensionless

Comment

Properties taken from M8 propellant from TM9-1300-214, except isochoric flame temperature from Campbell's Naval Weapons of WWII, specific force estimated based on the flame temperature and calorific value in Campbell's, and the burn rate variables from the M26E1 double base propellant in A060027, High Pressure Burning Rates of Multi-Base Propellants