عنوان مقاله [English]
In this paper, the combustion process in a prototype scramjet (DLR) is numerically simulated and studied. To that end, the scramjet is initially simulated and validated in the non-reacting condition. The results show that the method used has the ability to predict the fields of velocity and pressure with appropriate accuracy. Then, the same scramjet is simulated and validated for the reacting case by considering one-reaction model. The results of these two simulations illustrates that the maximum distance of subsonic area from the strut is 141 mm in the reacting case while this distance is only 22 mm in the non-reacting case. the waves pass through the jet region with a slight deviation in the non-reacting case while they are reflected after hitting the jet region in the reacting case.the waves pass through the jet region with a slight deviation in the non-reacting case while they are reflected after hitting the jet region in the reacting case.