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By Tripathi M. M., Kim J., Kim S.

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LeChuiton. Actuator Disc Modeling for Helicopter Rotors. Aerosp. Sci. Technol, 8:285–297, 2004. 33. A. Lovell. Aerodynamic Research to Support a Second Generation Supersonic Transport Aircraft - the EUROSUP Project. In ECCOMAS 1998, 1998. 34. A. Madrane, A. Raichle, and A. St¨ urmer. Parallel Implementation of a Dynamic Overset Unstructured Grid Approach. In ECCOMAS 2004, Jyv¨ askyl¨ a, Finland, July 2004. 35. S. Melber. 3D RANS Simulations for High-Lift Transport Aircraft Configurations with Engines.

Bartelheimer. An Improved Integral Equation Method for the Design of Transonic Airfoils and Wings. In AIAA 95-1688, 1995. 8. C. Braun, A. Bouche, and J. Ballmann. Numerical Study of the Influence of Dynamic Pressure and Deflected Ailerons on the Deformation of a High Speed Wing Model. In Krause. , W. Jaeger, and M. Resch, editors, High Performance Computing in Science and Engineering 2004. Springer Verlag, 2004. 9. J. R. Gauger. 2D and 3D Aerodynamic Shape Optimization Using Adjoint Approach. Aerosp.

A possibility to increase maximum lift is the usage of small delta wing like plates on the engine nacelles, the so-called nacelle strakes. These The MEGAFLOW Project – Numerical Flow Simulation for Aircraft 19 strakes generate vortices which run above the wing for high angles of attack. These vortices influence the wing and slat pressure distributions and shift the flow separations to higher angles of attack. At cruise flight conditions the strakes should not produce any significant additional drag.

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A basic inequality for submanifolds in locally conformal almost cosymplectic manifolds by Tripathi M. M., Kim J., Kim S.


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