Application of the VLM to the propulsive performance of a pair of oscillating wing-tails

Belibassakis, KA; Politis, GK; Triantafyllou, MS

dc.contributor.author	Belibassakis, KA	en
dc.contributor.author	Politis, GK	en
dc.contributor.author	Triantafyllou, MS	en
dc.date.accessioned	2014-03-01T02:48:30Z
dc.date.available	2014-03-01T02:48:30Z
dc.date.issued	1997	en
dc.identifier.issn	1369734X	en
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/33867
dc.relation.uri	http://www.scopus.com/inward/record.url?eid=2-s2.0-0030651870&partnerID=40&md5=c21c9b2feb17a2d99d83c070308e8907	en
dc.subject.other	Aspect ratio	en
dc.subject.other	Boundary conditions	en
dc.subject.other	Drag	en
dc.subject.other	Lift	en
dc.subject.other	Optimization	en
dc.subject.other	Oscillations	en
dc.subject.other	Performance	en
dc.subject.other	Unsteady flow	en
dc.subject.other	Viscosity	en
dc.subject.other	Wakes	en
dc.subject.other	Wings	en
dc.subject.other	Oscillating wing tails	en
dc.subject.other	Strouhal number	en
dc.subject.other	Vortex lattice technique	en
dc.subject.other	Aerodynamics	en
dc.title	Application of the VLM to the propulsive performance of a pair of oscillating wing-tails	en
heal.type	conferenceItem	en
heal.publicationDate	1997	en
heal.abstract	A 3-D unsteady vortex lattice technique is applied to the analysis of a pair of vertical oscillating wing tails, in order to investigate quantitatively its propulsive performance. Each lifting component undergoes a combined transverse and angular motion at the same frequency, in a uniform inflow condition. A free-wake analysis is incorporated in order to account for the effects of non-linearity, especially at increased amplitudes of oscillatory motion. Wing thickness effects are taken into account by an appropriate linearisation of the no-entrance boundary condition, and the effects of viscosity by means of a frictional drag coefficient applied to the solid surface. Numerical results are presented vs. experimental measurements for the propulsion thrust coefficient and the efficiency of the system over a range of motion parameters, including wing's aspect ratio, Strouhal number, feathering parameter and phase lag between oscillatory motions. These results indicate the significance of 3-D effects and show that the present technique, after appropriate elaboration, especially as concerns unsteady LE flow separation and stall effects, can serve for the design of this kind of propulsive systems with optimised performance.	en
heal.publisher	Computational Mechanics Publ, Southampton, United Kingdom	en
heal.journalName	Proceedings of the International Conference on Computational Methods and Experimental Measurements, CMEM	en
dc.identifier.spage	449	en
dc.identifier.epage	458	en