21–40 von 91 Ergebnissen
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    Boundary Layer Influence on Supersonic Jet/Cross-Flow Interaction in Hypersonic Flow

    Havermann, M. / Seiler, F. | Tema Archiv | 2006
    the resulting aerodynamic force is difficult, because the flowfield around such a jet in a hypersonic cross-flow is quite complex. In addition ...

    CFD Calculation of a Helicopter Rotor Hovering in Ground Effect

    Kutz, Benjamin M. / Bensing, Felix / Keßler, Manuel et al. | Tema Archiv | 2013
    approach. Tip vortex geometrical positions as well as thrust coefficients are scrutinized and compared to reference data in literature. Parameter ...

    Chimera simulation of a complete helicopter with rotors as actuator discs

    Chuiton, Frederic Le | Tema Archiv | 2006
    The EC-145 helicopter of Eurocopter Deutschland has been numerically investigated. How a Chimera grid system for the fuselage and both ...

    Chimera Simulations of Transported Large-Scale Vortices and Their Interaction with Airfoils

    Wolf, Christoph / Raichle, Axel / Knopp, Tobias et al. | Tema Archiv | 2010
    large distances and their interaction with an airfoil. While keeping the numerical dissipation at a minimum, the Chimera approach allows to ...

    Computation of Delta Wing Flap Oscillations with a Reynolds-Averaged Navier-Stokes Solver

    Allen, Alexander / Iatrou, Michail / Pechloff, Alexander et al. | Tema Archiv | 2006
    A selection of steady and unsteady validation results for the Reynolds-averaged Navier-Stokes solver FLM-NS with respect to an experimental ...

    Computation of the Flutter Boundary of the NLR 7301 Airfoil in the Transonic Range

    Voß, Ralph / Hippe, Carsten | Tema Archiv | 2006
    airfoil close to the transonic dip; Journal of Fluids and Structures 19 1-16, 2004] in the Transonic Wind Tunnel Göttingen (TWG). The comparison ...

    Computation of Trailing Edge Noise with a Discontinuous Galerkin Method

    Bauer, M. | Tema Archiv | 2010
    ). Results are compared with theory and Finite Difference (FD) computations. Next to the radiated sound field, special attention is paid to the ...

    Computations of Mixed and Displacement Ventilation in an Aircraft Cabin

    Webel, O. / Rütten, M. / Wagner, C. | Tema Archiv | 2013
    Steady and unsteady Reynolds-Averaged Navier Stokes Simulations are conducted to study mixed and displacement ventilation configurations in ...

    Delta Wing Steady Pressure Investigations for Sharp and Rounded Leading Edges

    Furman, Andrej / Breitsamter, Christian | Tema Archiv | 2006
    has been performed and the results for two different leading edge geometries (sharp and rounded) at three angles of attack are discussed in ...

    Detached-Eddy Simulation of Supersonic Flow Past Cylindrical Aft Body with and without Base Bleed

    Togiti, Vamshi / Breuer, Michael / Lüdeke, Heinrich | Tema Archiv | 2010
    In the present work supersonic base flows with and without base bleed are studied to investigate the influence of the bleed on the flow ...

    Detached-eddy simulation of the delta wing of a generic aircraft configuration

    Gurr, A. / Rieger, H. / Breitsamter, C. et al. | Tema Archiv | 2006
    In this paper, the results of a Detached-Eddy Simulation (DES) of the burst vortex system over a delta wing using a structured, locally ...

    Development of a Numerical Simulation Platform to Improve the Prediction of Helicopter Blade Vortex Interaction (BVI)

    Schneider, S. | Tema Archiv | 2013
    and trajectory. Moreover high fidelity turbulence modeling for instance LES schemes as well as the precise determination of the fluid ...

    Development of the Adjoint Approach for Aeroelastic Wing Optimization

    Abu-Zurayk, Mohammad / Brezillon, Joel | Tema Archiv | 2013
    and tested. The results showed that the approach can provide accurate sensitivities in a very efficient way. ...
    Schlagwörter: Fluid-Struktur-Wechselwirkung

    Effect of Differential Flap Settings on the Wake Vortex Evolution of Large Transport Aircraft

    Bellastrada, C. / Breitsamter, C. | Tema Archiv | 2006
    has been used to measure the wake vortex velocities at five cross stations up to 4.5 span distances downstream of the model. Results obtained ...

    Effect of Noise Reducing Modifications of the Slat on Aerodynamic Properties of the High-Lift System

    Ortmann, Judith / Wild, Jochen | Tema Archiv | 2006
    preliminary results. An optimization of slat chord length and brush length should be conducted to minimize C L, reduction. ...

    Experimental and Numerical Analysis of SHEFEX-II

    Barth, Tarik / Gehre, Rolf / Eggers, Thino et al. | Tema Archiv | 2013
    High Enthalpy Shock Tunnel Göttingen (HEG) are presented.The main focus is on the experimental and numerical investigation of the active ...

    Experimental and Numerical Modeling of Flow around Perforated Stabilizing Devices

    Chernukha, P.A. / Raffel, M. / Kalugin, V.T. | Tema Archiv | 2013
    surface and in a wake. Both experimental as well as numerical tests carried out at this early stage were aimed to estimate influence of ...

    Experimental investigation on periodic rolling of a delta wing flow at transonic Mach numbers

    Gölling, B. / Erne, O. | Tema Archiv | 2006
    Experimental simulation was conducted in the Transonic Wind-Tunnel Goettingen (TWG) of DNW with the 65° cropped delta wing AEROSUM model ...

    Experimental study on the Flowfield of a Delta-Canard-Configuration with Deflected Leading Edge

    Schmid, A. / Breitsamter, C. | Tema Archiv | 2006
    at a Re-number of 0.97.106 in a wind tunnel by hotwire anemometry. Leading edge flap settings of el.e. = 0 and el.e ...

    Extension of an Aeroelastic Coupling Environment to Aircraft Configurations with Rigid-Body Degrees of Freedom

    Wellmer, Georg / Behr, Marek / Ballmann, Josef | Tema Archiv | 2013
    -field solvers as well as the data exchange between them is outlined, and first steady coupled results are shown. ...