The characterization of pseudo-shock wave in various ducts with constant area

In a supersonic intake, the flow decelerates from supersonic to subsonic speed occurs inside the isolator by a series of bifurcated compression waves and followed by an adverse pressure gradient region. This wave phenomenon is referred to as pseudo-shock wave (PSW). The length of the PSW is one of the main consents in designing the Isolator. The flow characteristic of PSW is depending on the several parameters which makes the difficulties in designing the Isolator for each particular engine. Also, the pseudo shock wave strongly affects the performance of the flow device. In the present work, the characterization of the pseudo-shock wave is analyzed using computational fluid dynamics method in a constant area duct. The effect of back pressure on the shock structure and the influence of geometrical cross-sectional area are studied. The results show the nature of pseudo-shock wave is strongly influenced by the blockage ratio. The large aspect ratio duct shows relatively less total pressure loss. An improved correlation is obtained between the pressure ratio and the length of shock train region in terms of boundary layer blockage ratio. The estimated length of the shock train is compared with present numerical and reference experimental results. The results show a good agreement on predicting the length of shock train.