The design of a liquid propellant rocket engine thrust chamber requires the knowledge of the atomized droplet time of burning and its maximum flame sheet diameter so that the combustor length and diameter can be determined. In this work, the modified Spaldinq's analysis at supercritical pressure and temperature is presented. A computer program is coded to solve for the droplet time of burning and maximum flame sheet diameter. This code is used to solve five particular cases of those propellants which are used the most in rocket propulsion.