Complete burning of liquid propellants droplets is very important to avoid combustion instability and to get higher
specific impulse from liquid rocket engines. Combustion takes place in gaseous phase and reaction is fast. So, the
time consumed by a droplet for complete burning is the time taken by a droplet to get evaporated. An analytical
mono component fuel droplet evaporation model is developed and proposed for droplet evaporation in liquid rocket
engine based on heat and mass transfer. Effect of the fuel droplet curvature on vapor pressure is incorporated in the
model. The model is applied on a small-scale combustion chamber of bi-propellant liquid rocket engine where fuel
concentration away from droplet is not zero. A code is generated and applied. The results of the model show that
fuel droplet diameter, combustion chamber pressure, chamber diameter, mass flow rate and droplet relative velocity
with hot gas has significant effects on the life of droplet and characteristic length. Effects of chamber pressure and
diameter are more significant for larger droplet size.