[Picard]

hey, i am currently designing a rocket using a ammonium perchlorate as the oxidizer, aluminium as the fuel and HTPB as the binder, 68%,18%,14% respectively. i have been looking all over th place to try and find the Cp, thermal conductivity (k), and viscosity for this propellant or generally for any APCP and can't find it, as Ansys/Fluent requires these parameters to model my nozzle fluid flow accurately. if anyone could help me get find these values that would be helpful, also the burn rate equation for this propellant would be helpful too

thanks,

Leon