An experimental investigation of oblique wing static aeroelastic phenomena

A series of wind tunnel tests were conducted to determine the aerodynamic forces and moments produced by several clamped oblique wings. The wing sweep and aileron deflection angles were varied throughout a wide range of dynamic pressures. The wing structure was also stiffened. Strains were measured in the swept forward wing panels. Results from these tests showed that increasing the wing structural stiffness or applying aileron deflection would increase the wing divergence speed. The divergence speed decreased as the sweep angle increased. Further tests were conducted with the wing unconstrained in roll. Results showed that an oblique wing will attempt to unload its sweptforward panel by assuming a banked position. The wings were found to flutter before unclamped divergence occurred. Finally, it was found that the wing loading of an oblique wing can remain constant for a given aileron deflection throughout a wide range of velocities including velocities above the clamped divergence speed.

Name thesis:degree_name

Master of Science

Level thesis:degree_level

masters

Discipline thesis:degree_discipline

Aerospace and Ocean Engineering

Department dc:contributor.department

Aerospace and Ocean Engineering

Grantor dc:publisher

Virginia Tech

Year dc:date.issued

1975

Author dc:creator

• Papadales, Basil S.

Chair dc:contributor.committeechair

• Weisshaar, Terence A.

Committee members dc:contributor.committeemember

• Cliff, Eugene M.
• Schetz, Joseph A.

• aileron deflection
• wing structure

Statement dc:rights

• In Copyright

Licence dc:rights.uri

• http://rightsstatements.org/vocab/InC/1.0/

Dc Identifier Other

etd-06082010-020326

OAI identifier oai:identifier

oai:vtechworks.lib.vt.edu:10919/42938