Unsteady aerodynamic modelling: a simple state-space approach
2005 (English)In: Proc. of 43rd AIAA Annual Meeting and Exhibits, Reno, Nevada: AIAAA , 2005Conference paper (Refereed)
A simple mathematical prediction model for high angles of attack aerodynamics, including dynamic effect over delta wings, and an extension to full configuration is presented. The model presented is intended for application in conceptual design and is extended to parameters identifications in preliminary design with validation against experimental data. The aerodynamic model is based on leading edge suction analogy. In order to extend it to high angles of attack and dynamic motions, internal state variables are used to describe the different flow conditions, or state, over the wing/aircraft. In conceptual design the parameters used are determined from geometrical considerations and analogies with delta wings. To extend the mathematical mode to later design phases and augment the accuracy, the parameters are determined from wind tunnel data, in static case the present model has been extended to sideslip. The results obtained shows high accuracy in both static and dynamic cases.
Place, publisher, year, edition, pages
Reno, Nevada: AIAAA , 2005.
Engineering and Technology
IdentifiersURN: urn:nbn:se:liu:diva-31408DOI: 10.2514/6.2005-855Local ID: 17179OAI: oai:DiVA.org:liu-31408DiVA: diva2:252231
43rd AIAA Annual Meeting and Exhibits, Reno, Nevada, USA, 2005
Proceedings on CD2009-10-092009-10-092012-12-12