An approach to induced drag reduction and its experimental evaluation
2004 (English)Conference paper (Refereed)
An approach to minimize the induced drag of an aeroelastic configuration by means of multiple leading and trailing edge control surfaces is investigated. A computational boundary-element model is constructed and flap settings which reduce the induced drag predicted by the model are found by means of numerical optimization. Further, experiments with an elastic wind tunnel model are performed, showing both the potential for drag reduction and weaknesses of the simulation method employed.
Place, publisher, year, edition, pages
2004. 133-140 p.
, Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, ISSN 0273-4508
Aircraft, Boundary element method, Computer simulation, Drag, Fuel consumption, Maneuverability, Optimization, Pressure distribution, Reynolds number, Turbulent flow, Wind tunnels, Aeroelastic deformation, Drag reduction, Laminar boundary layer, Laminar-turbulent transition, Aerodynamic loads
IdentifiersURN: urn:nbn:se:kth:diva-157272ScopusID: 2-s2.0-16244418386OAI: oai:DiVA.org:kth-157272DiVA: diva2:771270
Collect. of Pap. - 45th AIAA/ASME/ASCE/AHS/ASC Struct., Struct. Dyn. and Mater. Conf.; 12th AIAA/ASME/AHS Adapt. Struct. Conf.; 6th AIAA Non-Deterministic Approaches Forum; 5th AIAA Gossamer Spacecraft Forum, 19 April 2004 through 22 April 2004, Palm Springs, CA, United States
QC 201412122014-12-122014-12-082014-12-12Bibliographically approved