AERODYNAMICS AND FLIGHT PERFORMANCE OF FLAPPING WING MICRO AIR VEHICLES

Persistent Link:
http://hdl.handle.net/10150/194755
Title:
AERODYNAMICS AND FLIGHT PERFORMANCE OF FLAPPING WING MICRO AIR VEHICLES
Author:
Silin, Dmytro
Issue Date:
2010
Publisher:
The University of Arizona.
Rights:
Copyright © is held by the author. Digital access to this material is made possible by the University Libraries, University of Arizona. Further transmission, reproduction or presentation (such as public display or performance) of protected items is prohibited except with permission of the author.
Abstract:
Research efforts in this dissertation address aerodynamics and flight performance of flapping wing aircraft (ornithopters). Flapping wing aerodynamics was studied for various wing sizes, flapping frequencies, airspeeds, and angles of attack. Tested wings possessed both camber and dihedral. Experimental results were analyzed in the framework of momentum theory. Aerodynamic coefficients and Reynolds number are defined using a reference velocity as a vector sum of a freestream velocity and a stroke-averaged wingtip velocity. No abrupt stall was observed in flapping wings for the angle of attack up to vertical. If was found that in the presence of a freestream lift of a flapping wing in vertical position is higher than the propulsive thrust. Camber and dihedral increased both lift and thrust. Lift-curve slope, and maximum lift coefficient increased with Reynolds number. Performance model of an ornithopter was developed. Parametric studies of steady level flight of ornithopters with, and without a tail were performed. A model was proposed to account for wing-sizing effects during hover. Three micro ornithopter designs were presented. Ornithopter flight testing and data-logging was performed using a telemetry acquisition system, as well as motion capture technology. The ability of ornithopter for a sustained flight and a presence of passive aerodynamic stability were shown. Flight data were compared with performance simulations. Close agreement in terms of airspeed and flapping frequency was observed.
Type:
text; Electronic Dissertation
Keywords:
aerodynamics; flapping; lift; performance; testing; wing
Degree Name:
Ph.D.
Degree Level:
doctoral
Degree Program:
Aerospace Engineering; Graduate College
Degree Grantor:
University of Arizona
Advisor:
Shkarayev, Sergey
Committee Chair:
Shkarayev, Sergey

Full metadata record

DC FieldValue Language
dc.language.isoenen_US
dc.titleAERODYNAMICS AND FLIGHT PERFORMANCE OF FLAPPING WING MICRO AIR VEHICLESen_US
dc.creatorSilin, Dmytroen_US
dc.contributor.authorSilin, Dmytroen_US
dc.date.issued2010en_US
dc.publisherThe University of Arizona.en_US
dc.rightsCopyright © is held by the author. Digital access to this material is made possible by the University Libraries, University of Arizona. Further transmission, reproduction or presentation (such as public display or performance) of protected items is prohibited except with permission of the author.en_US
dc.description.abstractResearch efforts in this dissertation address aerodynamics and flight performance of flapping wing aircraft (ornithopters). Flapping wing aerodynamics was studied for various wing sizes, flapping frequencies, airspeeds, and angles of attack. Tested wings possessed both camber and dihedral. Experimental results were analyzed in the framework of momentum theory. Aerodynamic coefficients and Reynolds number are defined using a reference velocity as a vector sum of a freestream velocity and a stroke-averaged wingtip velocity. No abrupt stall was observed in flapping wings for the angle of attack up to vertical. If was found that in the presence of a freestream lift of a flapping wing in vertical position is higher than the propulsive thrust. Camber and dihedral increased both lift and thrust. Lift-curve slope, and maximum lift coefficient increased with Reynolds number. Performance model of an ornithopter was developed. Parametric studies of steady level flight of ornithopters with, and without a tail were performed. A model was proposed to account for wing-sizing effects during hover. Three micro ornithopter designs were presented. Ornithopter flight testing and data-logging was performed using a telemetry acquisition system, as well as motion capture technology. The ability of ornithopter for a sustained flight and a presence of passive aerodynamic stability were shown. Flight data were compared with performance simulations. Close agreement in terms of airspeed and flapping frequency was observed.en_US
dc.typetexten_US
dc.typeElectronic Dissertationen_US
dc.subjectaerodynamicsen_US
dc.subjectflappingen_US
dc.subjectliften_US
dc.subjectperformanceen_US
dc.subjecttestingen_US
dc.subjectwingen_US
thesis.degree.namePh.D.en_US
thesis.degree.leveldoctoralen_US
thesis.degree.disciplineAerospace Engineeringen_US
thesis.degree.disciplineGraduate Collegeen_US
thesis.degree.grantorUniversity of Arizonaen_US
dc.contributor.advisorShkarayev, Sergeyen_US
dc.contributor.chairShkarayev, Sergeyen_US
dc.contributor.committeememberTumin, Anatolien_US
dc.contributor.committeememberWygnanski, Israelen_US
dc.contributor.committeememberSprinkle, Jonathanen_US
dc.identifier.proquest11305en_US
dc.identifier.oclc752261151en_US
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