The recent advances in aerospace vehicle technology demands the
best possible propulsive balance to provide better thrust and
minimum drag. Air-breathing engines are the best choice for the
propulsion due to its minimum weight. The efficiency of such
engines depend upon the quality of air entering for combustion.
This book provides complete flow analysis of both pure
inline-compression and mixed-compression inlets. Two dimensional
simulations were carried out with SST k- model using FLUENT. The
boundary layer formed inner side of the engine had an adverse
pressure gradient on the ramp producing a boundary layer
separation. Due to this the boundary layer thickens and the static
pressure starts to decrease whose effect leads till the trailing
edge of inlet. Small wedge shaped Micro-Vortex Generator (MVG)
inside the inlet smoothen the generated shock-boundary layers and
thereby an efficient compression is obtained . The analysis should
help shed some light on hypersonic inlet design optimization at
off-design condition and should be especially useful to researchers
and academicians in the field of Aerospace Engineering."
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