Evaluation of a simplified grid treatment for oscillating trailing-edge control surfaces Export

@article{Rampurawala2007, abstract = {The aeroelastic behavior associated with control surfaces is of particular practical interest. The treatment of the control surface in a computational fluid dynamics based simulation is complicated by the change in topology of the geometry as the flap edge is exposed. This paper evaluates the use of a treatment which blends the flap edge into the wing. This simplifies the mesh treatment by avoiding topological changes. The influence of the treatment of the forced flap motions on the aerodynamic responses of the rigid benchmark active control technology wing and a flexible supersonic transport wing is evaluated. Comparison is made with results obtained when the flap edge is exposed. It is shown that the predictions from the blended treatment give similar results, including local effects on the control surface, to calculations which include the flap edge effects.}, address = {Computational Fluid Dynamics Laboratory, Flight Sciences and Technology, Department of Engineering}, author = {Rampurawala, A. M. and Badcock, K. J.}, citeulike-article-id = {2859326}, citeulike-linkout-0 = {http://dx.doi.org/10.2514/1.24623}, citeulike-linkout-1 = {http://www.scopus.com/record/display.url?view=extended&origin=resultslist&eid=2-s2.0-34548328262}, doi = {10.2514/1.24623}, journal = {Journal of Aircraft}, keywords = {3d, cosdyna, flap, simulation, supersonic, transonic, urans}, number = {4}, pages = {1177--1188}, posted-at = {2008-06-03 16:06:10}, priority = {2}, title = {Evaluation of a simplified grid treatment for oscillating trailing-edge control surfaces}, url = {http://dx.doi.org/10.2514/1.24623}, volume = {44}, year = {2007} }

TY - JOUR ID - Rampurawala2007 L3 - citeulike-article-id:2859326 N2 - The aeroelastic behavior associated with control surfaces is of particular practical interest. The treatment of the control surface in a computational fluid dynamics based simulation is complicated by the change in topology of the geometry as the flap edge is exposed. This paper evaluates the use of a treatment which blends the flap edge into the wing. This simplifies the mesh treatment by avoiding topological changes. The influence of the treatment of the forced flap motions on the aerodynamic responses of the rigid benchmark active control technology wing and a flexible supersonic transport wing is evaluated. Comparison is made with results obtained when the flap edge is exposed. It is shown that the predictions from the blended treatment give similar results, including local effects on the control surface, to calculations which include the flap edge effects. IS - 4 JF - Journal of Aircraft AD - Computational Fluid Dynamics Laboratory, Flight Sciences and Technology, Department of Engineering EP - 1188 TI - Evaluation of a simplified grid treatment for oscillating trailing-edge control surfaces VL - 44 SP - 1177 KW - 3d KW - cosdyna KW - flap KW - simulation KW - supersonic KW - transonic KW - urans AU - Rampurawala, AM AU - Badcock, KJ PY - 2007/// UR - http://dx.doi.org/10.2514/1.24623 ER -