CFD Analysis of Jet Plume Shock and Sonic Boom Signatures Interaction with Different Nozzle Pressure Ratios

A complete Reynolds Averaged Navier-Stokes solution of supersonic aircraft is conducted to study the nozzle plume effects on the external aerodynamics of the supersonic vehicle. Different nozzle pressure ratios are used to simulate the supersonic flow for detail study of supersonic flow behavior around vehicle in the presence of jet plume. It is found that Plume at different nozzle pressure ratio changed the flow structure around vehicle and its sonic boom signature strength. The strength of sonic boom signature is varied with the change of nozzle pressure ratios. It is observed that highly under-expanded jet plume of nozzle produces very steeper shock which reduces the dip of sonic boom N-wave signature. In this effort structure of plumes for different nozzle pressure ratios are also investigated. It is observed that higher order schemes of minimum second order are to be used to capture the free shear layers, shock train and mixing layers.