Heat capacity of rocket propellant (RP-1 fuel) at high temperatures and high pressures

Abstract

Isobaric heat capacity of rocket propellant (RP-1 fuel) has been measured with a vacuum adiabatic calorimeter immersed in a precision liquid thermostat. Measurements were made in the temperature range from 293 to 671 K and at pressures up to 60 MPa. The uncertainty of heat capacity, pressure, and temperature measurements were estimated to be 2–2.5%, 0.05%, and 15 mK, respectively. The measured values of heat capacity were compared with the values calculated from a surrogate mixture model (equation of state, EOS). The average absolute deviation (AAD) between the present data and the values calculated with EOS was 0.81%.