As is known, jet propulsion fuels are rather complex with combustion resulting in a vast range of chemical compounds. So, their real modeling is rather hard and the application of final constructed models is restricted to a narrow band of real propulsion jet fuels. The main objective of this study is to extend suitable surrogate fuel models to reliably predict the combustion and soot characteristics of the equivalent jet propulsion fuel. In this regard, the combustion of proposed surrogate fuels is numerically studied in the above chosen combustion chamber. Of importance, the surrogate fuels should be proposed suitably to represent the correct physical characteristics and the real chemical behaviors of the main jet propulsion fuel. To achieve these important points, different surrogate fuels are used to study the combustion process in the chosen JP combustor. The achieved numerical results are compared with experimental data. To be sure of equivalent characteristic between the jet propulsion fuel and the proposed surrogate fuels, we carry out the comparisons for not only the flame structures but also their soot formations. In this regard, the study is conducted for the distributions of mixture fraction, temperature, and soot volume fraction at different axial locations inside the combustor. The current study shows that the extended surrogate fuels reliably predict the combustion and soot characteristics of the equivalent jet aviation. © 2018 by G.E. Schneider. Published by the American Institute of Aeronautics and Astronautics, Inc.