Approach to Induced Drag Reduction with Experimental Evaluation
2005 (English)In: Journal of Aircraft, ISSN 0021-8669, Vol. 42, no 6, 1478-1485 p.Article in journal (Refereed) Published
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 model based on a boundary-element method is constructed and drag-reducing flap settings are found by means of numerical optimization. Further, experiments with an elastic wind-tunnel model are performed in order to evaluate the numerically obtained results. Induced-drag results are obtained by analyzing lift distributions computed from optically measured local angles of attack because standard techniques proved insufficient. Results show that significant reductions of induced drag of flexible wings can be achieved by using optimal control surface settings.
Place, publisher, year, edition, pages
2005. Vol. 42, no 6, 1478-1485 p.
Aeroelastic configuration; Drag reduction; Flap settings; Lift distributions
Engineering and Technology
IdentifiersURN: urn:nbn:se:kth:diva-7268DOI: 10.2514/1.11713ISI: 000233846200012ScopusID: 2-s2.0-29544442463OAI: oai:DiVA.org:kth-7268DiVA: diva2:12227
QC 20100531. Konferens: AIAA/ASME/ASCE/AHS/ASC 45th Structures, Structural Dynamics and Materials Conference Palm Springs, CA, APR 19-22, 20042007-06-012007-06-012011-12-08Bibliographically approved