Titlebook: New Results in Numerical and Experimental Fluid Mechanics VI; Contributions to the Cameron Tropea,Suad Jakirlic,Heinz Hönlinger Conference

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1612-2909 . Symposium of the STAB (German Aero-space Aerodynamics Association). In this association all those German scientists and engineers from universities, research establishments and industry are involved, who are doing research and project work in numerical and experimental fluid mechanics and aerodyna

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URANS and DES Simulation of Flow Around a Rectangular Cylindering the basic unsteady flow phenomena in the considered cases. These results are further confirmed by the DES method, which provides information about the instantaneous flow variables and offers a deeper insight into the flow physics.

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Numerical Simulation of a Wing with a Gapless High-Lift System Using Circulation Controlystems. The promising results of the 2D simulations motivate applications to a wing-body configuration. The results show that a gapless high-lift system equipped with circulation control has the ability to provide sufficient lift for take off, climb and landing.

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Design of a Retrofit Winglet for a Transport Aircraft with Assessment of Cruise and Ultimate Structu evaluate ultimate structural loading. Comparing the results of the rigid wing with the deformed wing the wing root bending moment and the bending moment of the device is clearly reduced for the deformed wing. Thereby the advantage to which an implementation of the described method for future design processes would lead becomes apparent.

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An Airbrake Design Methodology for Steep Approachesng mounted over the wing region, dorsal airbrakes utilise the accelerated flow field around the airframe and generate a high amount of drag. Neither the lift nor the pitch-moment are influenced considerably through deployment of the dorsal airbrakes. This paper presents a methodology and principles

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Studies on Tailplane Stall for a Generic Transport Aircraft Wind Tunnel Modeld Reynoldsaveraged Navier Stokes Code TAU, are in good agreement with the experiments. They show a separation of the boundary layer starting at the trailing edge with high crossflow velocities at the outer tailplane. Depending on the boundary-layer transition, the stall occurs abruptly for natural t

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