Abstract: Two line element (TLE) released by North American Aerospace Defense Command (NORAD) is widely used by aerospace workers, and the matched SGP4/SDP4 (Simplified General Perturbation Version 4/Simplified Deep-space Perturbation Version 4) model is used to propagate it. Nevertheless, no corresponding information of accuracy and covariance is clearly given, thus the application in TLE data is greatly restricted. In this paper, the determined and predicted orbits are compared to generate orbital error data, based on the historical TLE from the Space-Track website and SGP4/SDP4 model. By dividing different time bins, the fitting coefficients of each space object's orbit prediction error variation are given, and the characteristics of error evolution in different orbits are further discussed. The mean analysis models of orbit prediction error evolution with time for four orbit types of targets are given, which provides a valuable reference for expanding the application of TLE data.