DLR Scramjet Model Analysis

A schematic diagram of DLR scramjet model [7-9] is described in Fig. 1.The air enters into combustion chamber at M=2.0 whereas hydrogen fuel (H2) is injected parallel to the air stream at M =1.0. The width and height of the combustor section at the entrance is 40 mm and 50 mm respectively which is then diverged at an angle of 3ο on the upper wall of the combustor. The strut is 32 mm long and 6mm height which are located at a distance of 77 mm from the entrance. The boundary conditions of Waidmann et al. [7-9] are only used for the purpose of validation in case of single strut. Regarding the remaining operating conditions and detailed phenomena about experiment are given in Waidmann et al. [7-9]. For reducing the computational cost and design
Species transport [23] along with finite rate chemistry model as well as eddy dissipation reaction model [23,
24, and 25] is the combustion model which is mainly used in the current research work. These models are preferred due to their simplicity and apparently precise modeling of the burned gas containing completely oxidized species of hydrogen (H2) fuel.
The H2-air mechanism has only a minimal impact on the mean flow properties in the reacting flow field
[26], particularly the wall pressure arrangement
[27,39] and the Finite-rate along with Eddydissipation model has been explained to be more accurate for the reaction flow-field simulation as compared to Eddy-dissipation model [28]. As the main priority of the present research work is to investigate the effect two as well as three struts on the combustion improvement of scramjet engine, therefore the influence of more intricate chemical reaction dynamics such as hydrogen chemistry along with number of stages kinetic mechanisms [29] will be discussed later and it is confirmed that the single step chemical reaction is sufficient to perform the overall parameter evaluation for the combustion of
scramjet