Parametric aeroelastic modeling, maneuver loads analysis using CFD methods and structural design of a fighter aircraft

The DLR Future Fighter Demonstrator (FFD) is a highly agile, two-seated aircraft with twin-engines equipped, reheat and design flight speed extending into the supersonic regime (up to Ma=2.0). Based on given conceptual design, presented work focuses aeroelastic modeling, including structures, masses aerodynamics. Using models, comprehensive loads analysis 688 maneuver load cases, covering whole envelope, performed. Comparing results obtained from aerodynamic panel methods (VLM ZONA51) higher fidelity CFD, necessity of CFD based in preliminary such fighter configuration shown, as it leads physically different well loads. rigorous application heavy burden during but this demonstrates that doable today. Finally, model subject structural optimization, demonstrating differences result heavier primary net mass ≈3.3t for approach ≈4.1t approach. Because all remaining models are unchanged, difference can be clearly attributed physical flow solutions CFD.