The focus of this research proposal is the investigation of the aeroelastic effects of a flexible lift augmentation system (LAS) wing. This research involves characterization of the forced vibration response of a wing appendage used to augment short field take off and landing (STOL) operations.
Although flutter theory is now well understood, the LAS presents the complications of a highly deformable airfoil shape as well as larger structural damping values compared to metal wings.
The proposed research will involve derivation of the equations of motion aided by experimental data from nodal excitation of the wing; stiffness and rigidity modeling from static wing loading and collection of flight test data to characterize the potential flow around the membrane wing.
The knowledge gained from this research will be of critical importance in assuring the safety of flight by identifying the critical flutter speeds, as well as establishing a good basis for the structural design of future lift augmentation structures.
","abstract_html":"<p>The focus of this research proposal is the investigation of the aeroelastic effects of a flexible lift augmentation system (LAS) wing. This research involves characterization of the forced vibration response of a wing appendage used to augment short field take off and landing (STOL) operations.</p> <p>Although flutter theory is now well understood, the LAS presents the complications of a highly deformable airfoil shape as well as larger structural damping values compared to metal wings.</p> <p>The proposed research will involve derivation of the equations of motion aided by experimental data from nodal excitation of the wing; stiffness and rigidity modeling from static wing loading and collection of flight test data to characterize the potential flow around the membrane wing.</p> <p>The knowledge gained from this research will be of critical importance in assuring the safety of flight by identifying the critical flutter speeds, as well as establishing a good basis for the structural design of future lift augmentation structures.</p>","abstract_has_math":false,"creators":["Wanjohi, Isaac Nguri"],"institution":null,"degree_name":"Master of Science in Aerospace Engineering","degree_level":"Thesis - Open Access","degree_discipline":"Aerospace Engineering","degree_department":null,"school":null,"contributors":["James Ladesic","Jean-Michel Dhainaut","Richard P. Anderson"],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2004,"date_issued":"2004-07-01T07:00:00Z","date_published":"2004-07-01T07:00:00Z","updated_at":"2026-07-27T19:25:29Z","subjects":["aeroelastic","flexible","membrane","wing","Aerospace Engineering","Systems Engineering and Multidisciplinary Design Optimization"],"languages":[],"rights":[],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"https://commons.erau.edu/db-theses/209","outbound_label":"Repository record","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["James Ladesic","Jean-Michel Dhainaut","Richard P. Anderson"]},{"key":"dc:creator","label":"Author","values":["Wanjohi, Isaac Nguri"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"thesis:degree_discipline","label":"Discipline","values":["Aerospace Engineering"]},{"key":"thesis:degree_level","label":"Degree Level","values":["Thesis - Open Access"]},{"key":"thesis:degree_name","label":"Degree Name","values":["Master of Science in Aerospace Engineering"]}]},{"id":"subjects_keywords","label":"Subjects and Keywords","entries":[{"key":"dc:subject","label":"Dc Subject","values":["aeroelastic","flexible","membrane","wing","Aerospace Engineering","Systems Engineering and Multidisciplinary Design Optimization"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["https://commons.erau.edu/db-theses/209"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description.abstract","label":"Abstract","values":["The focus of this research proposal is the investigation of the aeroelastic effects of a flexible lift augmentation system (LAS) wing. This research involves characterization of the forced vibration response of a wing appendage used to augment short field take off and landing (STOL) operations.
Although flutter theory is now well understood, the LAS presents the complications of a highly deformable airfoil shape as well as larger structural damping values compared to metal wings.
The proposed research will involve derivation of the equations of motion aided by experimental data from nodal excitation of the wing; stiffness and rigidity modeling from static wing loading and collection of flight test data to characterize the potential flow around the membrane wing.
The knowledge gained from this research will be of critical importance in assuring the safety of flight by identifying the critical flutter speeds, as well as establishing a good basis for the structural design of future lift augmentation structures.
"]},{"key":"dc:title","label":"Title","values":["Aeroelastic Analysis of a Flexible Membrane Wing"]}]}],"canonical_facts":{"dc:contributor":["James Ladesic","Jean-Michel Dhainaut","Richard P. Anderson"],"dc:creator":["Wanjohi, Isaac Nguri"],"dc:description.abstract":["The focus of this research proposal is the investigation of the aeroelastic effects of a flexible lift augmentation system (LAS) wing. This research involves characterization of the forced vibration response of a wing appendage used to augment short field take off and landing (STOL) operations.
Although flutter theory is now well understood, the LAS presents the complications of a highly deformable airfoil shape as well as larger structural damping values compared to metal wings.
The proposed research will involve derivation of the equations of motion aided by experimental data from nodal excitation of the wing; stiffness and rigidity modeling from static wing loading and collection of flight test data to characterize the potential flow around the membrane wing.
The knowledge gained from this research will be of critical importance in assuring the safety of flight by identifying the critical flutter speeds, as well as establishing a good basis for the structural design of future lift augmentation structures.
"],"dc:identifier":["https://commons.erau.edu/db-theses/209"],"dc:subject":["aeroelastic","flexible","membrane","wing","Aerospace Engineering","Systems Engineering and Multidisciplinary Design Optimization"],"dc:title":["Aeroelastic Analysis of a Flexible Membrane Wing"],"thesis:degree_discipline":["Aerospace Engineering"],"thesis:degree_level":["Thesis - Open Access"],"thesis:degree_name":["Master of Science in Aerospace Engineering"]},"updated_at":"2026-07-27T19:25:29Z"}