In this paper a typical combat aircraft fuel jettisoning system is considered for analysis by means of Modeling and Simulation Techniques, since the proposed fuel jettisoning outlet is in an uncommon location (extreme end of rear fuselage) due to design constrains imposed by flight control surfaces (Elevon) and wing structures. Detailed analysis has been performed using lowmaster and CFD to assess the performance and safety of the proposed fuel jettisoning system.
In the performance analysis, pressure vs. flow characteristics of the fuel jettisoning system is established by varying the intensity of pressure source between 3.5 Psig to 6.5 Psig and Engine power settings between idle to maximum after burner power.
In the safety analysis, CFD analysis has been performed for various fuel jettison outlet configurations in cruise flight condition and its performance was analyzed considering the influence of Engine plume parameters (with and without Engine Plume effects). Through the implementation of modeling and simulation approach an optimum outlet configuration was arrived for further implementation on aircraft.
From this simulation results, safe flight test points were derived. Subsequently, experimental flight tests were carried out and verified the in-flight performance of fuel jettisoning system.