Parametric Simulation on Reduction of $S$ -Band Rear Bistatic Radar Cross Section of Jet Engine With Vector Thrust Nozzle via Plasmatized Exhaust

The feasibility of using plasmatized exhaust to reduce engine rear bistatic radar cross section (RCS) is studied. The possible range of plasma density inside a jet engine when alkaline additives are used in fuel is analyzed via the Saha equation, and the results show that there should be high density plasma. Next, the S-band rear bistatic RCS of a jet engine with or without the vector thrust nozzle is simulated using a finite-difference time-domain code. Then, the RCS when exhaust is plasmatized is simulated to make comparison. The results show that even with low density plasma, the effective shape of the vector thrust nozzle is changed, and the RCS is reduced. As the plasma density becomes higher, the reflection becomes stronger and the radar wave penetration into the plasmatized exhaust becomes less. The change in RCS is strongly related to the direction and shape of the jet exhaust, besides the plasma density.