Theoretical analysis of perching and hovering maneuvers

Ramesh, K. , Gopalarathnam, A., Edwards, J.R., Granlund, K. and Ol, M.V. (2013) Theoretical analysis of perching and hovering maneuvers. In: 43rd AIAA Fluid Dynamics Conference and Exhibit, San Diego, CA, USA, 24-27 Jun 2013, (doi: 10.2514/6.2013-3194)

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Unsteady aerodynamic phenomena are encountered in a large number of modern aerospace and non-aerospace applications. Leading edge vortices (LEVs) are of particular interest because of their large impact on the forces and performance. In rotorcraft applications, they cause large vibrations and torsional loads (dynamic stall), affecting the performance adversely. In insect flight however, they contribute positively by enabling high-lift flight. Identifying the conditions that result in LEV formation and modeling their effects on the flow is an important ongoing challenge. Perching (airfoil decelerates to rest) and hovering (zero freestream velocity) maneuvers are of special interest. In earlier work by the authors, a Leading Edge Suction Parameter (LESP) was developed to predict LEV formation for airfoils undergoing arbitrary variation in pitch and plunge at a constant freestream velocity. In this research, the LESP criterion is extended to situations where the freestream velocity is varying or zero. A point-vortex model based on this criterion is developed and results from the model are compared against those from a computational fluid dynamics (CFD) method. Abstractions of perching and hovering maneuvers are used to validate the low-order model's performance in highly unsteady vortex-dominated flows, where the time-varying freestream/translational velocity is small in magnitude compared to the other contributions to the velocity experienced by the leading edge region of the airfoil. Time instants of LEV formation, flow topologies and force coefficient histories for the various motion kinematics from the low-order model and CFD are obtained and compared. The LESP criterion is seen to be successful in predicting the start of LEV formation and the point-vortex method is effective in modeling the flow development and forces on the airfoil. Typical run-times for the low-order method are between 30-40 seconds, making it a potentially convenient tool for control/design applications.

Item Type:Conference Proceedings
Glasgow Author(s) Enlighten ID:Ramesh, Dr Kiran
Authors: Ramesh, K., Gopalarathnam, A., Edwards, J.R., Granlund, K., and Ol, M.V.
College/School:College of Science and Engineering > School of Engineering > Autonomous Systems and Connectivity
Copyright Holders:Copyright © 2013 American Institute of Aeronautics and Astronautics
Publisher Policy:Reproduced in accordance with the copyright policy of the publisher

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Project CodeAward NoProject NamePrincipal InvestigatorFunder's NameFunder RefLead Dept
9550Theoretical, Computational, and Experimental Studies of the Aerodynamics of Perching FlightDr. Ashok GopalarathnamAFOSRUNSPECIFIED