Rocket
propellants are
subjected to extreme thermodynamic conditions in high-performance
liquid rocket engines, with temperatures in excess of 700 K and pressures
nearing 100 MPa. Knowledge of the fuel viscosity is crucial for modeling
the performance of liquid rocket engines utilizing rocket grade kerosene
rocket propellant 1 (RP-1) or RP-2. The present study reports the
viscosity of two RP-2 fuel samples at temperatures from 298 to 573
K and pressures up to 100 MPa. A high-temperature, high-pressure (HTHP),
variable-volume, close-clearance, windowed, rolling-ball viscometer
is used to measure the viscosity based on terminal velocity and RP-2
density. To facilitate the use of the RP-2 viscosity data with computational
fluid dynamics (CFD) and other analytical models, these data are modeled
with the free volume theory (FVT), with an empirical temperature/pressure-dependent
correlation and with a modified form of the Vogel–Fulcher–Tammann
(VFT) equation.