Abstract Title

Airfoil Aeroelasticity

Author Information

Yunxiao LiuFollow

Is this project an undergraduate, graduate, or faculty project?

Undergraduate

individual

Poster Session

Authors' Class Standing

Yunxiao Liu, Senior

Lead Presenter's Name

Yunxiao Liu

Faculty Mentor Name

Mandar Kulkarni

Abstract

Aeroelasticity is the relationship between a structure’s elastic response to the fluid flowing over it. Aircraft structures must be strong and lightweight. Sometime the tradeoff results in structures that exhibit a strong coupling between their elastic and fluid responses. At high aircraft speeds, such an aeroealstic response may have a negative effect on the structures’ intended aerodynamic, structural, and stability parameters. The goal of this research is to find if unfavorable aeroelastic responses can be reduced with changes in geometry of the aircraft. Continuum Sensitivity Analysis is used to obtain the derivatives or aeroelastic response of a flexible airfoil with respect to the geometry parameters of the airfoil. SU2, a fluid solver, finds the pressure on an airfoil by modeling the airfoil and a large surrounding area as a mesh. Hundreds of sub-iterations are required to converge to an accurate value for pressure and lift. Then, NASTRAN software finds the deformation or elastic response of the structure due to the pressure applied to it from the flow solver. This process of running SU2 and then NASTRAN must be iterated until static equilibrium is reached, eventually converging to a shape that represents the airfoil's deformation due to pressure from the airflow.

Did this research project receive funding support (Spark or Ignite Grants) from the Office of Undergraduate Research?

No

Share

COinS
 

Airfoil Aeroelasticity

Aeroelasticity is the relationship between a structure’s elastic response to the fluid flowing over it. Aircraft structures must be strong and lightweight. Sometime the tradeoff results in structures that exhibit a strong coupling between their elastic and fluid responses. At high aircraft speeds, such an aeroealstic response may have a negative effect on the structures’ intended aerodynamic, structural, and stability parameters. The goal of this research is to find if unfavorable aeroelastic responses can be reduced with changes in geometry of the aircraft. Continuum Sensitivity Analysis is used to obtain the derivatives or aeroelastic response of a flexible airfoil with respect to the geometry parameters of the airfoil. SU2, a fluid solver, finds the pressure on an airfoil by modeling the airfoil and a large surrounding area as a mesh. Hundreds of sub-iterations are required to converge to an accurate value for pressure and lift. Then, NASTRAN software finds the deformation or elastic response of the structure due to the pressure applied to it from the flow solver. This process of running SU2 and then NASTRAN must be iterated until static equilibrium is reached, eventually converging to a shape that represents the airfoil's deformation due to pressure from the airflow.

 

To view the content in your browser, please download Adobe Reader or, alternately,
you may Download the file to your hard drive.

NOTE: The latest versions of Adobe Reader do not support viewing PDF files within Firefox on Mac OS and if you are using a modern (Intel) Mac, there is no official plugin for viewing PDF files within the browser window.