The present study primarily concerns itself to validate the novel technique presented by Vijay and Ramakrishna (2020) to predict the initial temperature sensitivity of non-aluminized composite propellant compositions. The technique is used here to predict the combustion characteristics of non-aluminized propellants with 86% loading. The coarse to fine ratio of 1:1 and 4:1 for the AP particles was used in theses propellants. The burn rate and temperature sensitivity of these propellants were determined experimentally and compared with the computed ones. A reasonable match was found between the predicted and experimentally obtained values.