Design and Analysis of Generic Hypersonic Scramjet Inlets

A new methodology has been developed for the design of hypersonic scramjet inlets using\ud gas dynamic relations. The approach aims to find the optimal inlet geometry which has\ud maximum total pressure recovery at a prescribed design free stream Mach number. The\ud design criteria for inlet is chosen as shock-on-lip condition which ensures maximum capture\ud area and minimum intake length. Designed inlet geometries are simulated using CFD\ud analysis. The effects of 1D, 2D, inviscid and viscous effects on performance of scramjet\ud inlet are reported here. A correction factor in inviscid design is reported for viscous effects\ud to obtain shock-on-lip condition. A parametric study is carried out for the effect of throat\ud Mach number in the design of scramjet inlets. Present results show that 2D and viscous\ud effects are significant on performance of scramjet inlet. Performance analysis of scramjets\ud inlets has also been performed. Two planar inlets Mach 10.4 and Mach 7 are considered and\ud the effects of wall cooling, off design and cowl height on the performance of the scramjet\ud inlets are reported. Various performance parameters of scramjet inlets are reported with\ud different operating conditions. Maximum temperatures attained in the inlets are given.\ud Results show that the surface temperature and the cowl height have a significant effect on\ud performance of scramjet inlet. The total pressure recovery coefficient and the spillage losses\ud are reported at different free stream Mach numbers. External flow field analysis is carried\ud out and coefficients of drag and lift are reported here. The Present results are matching\ud well with the experimental results available in the literature