This study uses a computer simulation of a strapdown laser gyro inertial reference system to analyze the errors generated as a result of highly dynamic flight profiles. A stochastic error model using state-of-the-art inertial sensors is developed in detail and implemented in software. SOFE, a generalized simulation program, was used to implement both a Monte Carlo simulation and a covariance analysis. The Monte Carlo method was selected to perform the error analysis. Two highly dynamic flight trajectories were developed using the flight profile generator, PROFGEN. The PROFGEN program itself was modified to include an aircraft roll time constant and a roll-only maneuver. The errors generated in the inertial reference system as a result of these flight trajectories were investigated. Both an error budget and an analysis of the maneuvers inducing these errors were accomplished. Gyro error sources induced the most system error and coupled the dynamics of the flight trajectory into the variations of the error. Misalignment was found to be the major cause of both the accelerometer and gyro induced error. Successive maneuvers were found that reinforced system errors and other maneuvers were found that cancelled these errors. Also, some cases were found where the amount of system error varied with a change in heading.