The design of modern fighter aircraft configurations is mainly driven by constrains of low observability, high maneuverability and good supersonic flight characteristics. The aerodynamic requirements of modern fighter aircraft can be fulfilled by delta wing planforms. The medium to high leading edge sweep angles of these configurations lead to a complex vortical flow field and challenging aerodynamic behavior. The complex and, especially at high angles of attack, often unsteady flow fields can only be reliably predicted by (unsteady) RANS or scale resolving methods. Examples are given by Sch¨utte and Hummel [1] [2] and Werner et al [3]. Over the past decades, a series of defense projects have been established at DLR to study the vortical flow physics, aerodynamic behavior, and performance of fighter type onfigurations, and to develop best practices for the numerical simulation of these challenging flows. The test cases investigated by DLR covered the entire Mach number range relevant to these kinds of aircraft, as well as a broad range of different geometric configurations. This experience finally resulted in the recent capabilities to design a fully configured generic fighter configuration within the DLR projects Diabolo and WingMates. The objectives of this study are to enhance the understanding of the flow physics and aerodynamic behavior of fighter aircrafts and to provide a fighter design that meets required performance, such as agility in sub-, trans- and supersonic flight conditions. To achieve this goal, both URANS and scale resolving simulations are carried out and compared against each other to assess their respective roles in the design process of modern combat aircraft configurations.