#### Title of Oral/Poster Presentation

A Generalization of Thin-Airfoil Theory for Infinite Wings with Sweep

#### Class

Article

#### College

College of Engineering

#### Faculty Mentor

Douglas Hunsaker

#### Presentation Type

Oral Presentation

#### Abstract

Thin-airfoil theory predicts a reduction of section lift when sweep is applied to an infinite wing. This prediction assumes the airfoil sections of the wing are of negligible thickness and the angle of sweep and angle of attack of the wing are small. By relaxing these assumptions, the prediction of section lift of an infinite wing with sweep is generalized to account for a larger variation in airfoil geometry, wing sweep, and flight conditions. The generalized equations derived from the relaxed assumptions are applied to a vortex panel method to obtain section lift predictions for a range of NACA 4-digit airfoils. In an effort to obtain an analytic relationship between the section lift produced by infinite wings with and without sweep, the section lift predictions produced by the vortex panel method are fit to empirical equations. The results are compared to data computed using computational fluid dynamics software.

#### Location

Room 421

#### Start Date

4-12-2018 9:00 AM

#### End Date

4-12-2018 10:15 AM

A Generalization of Thin-Airfoil Theory for Infinite Wings with Sweep

Room 421

Thin-airfoil theory predicts a reduction of section lift when sweep is applied to an infinite wing. This prediction assumes the airfoil sections of the wing are of negligible thickness and the angle of sweep and angle of attack of the wing are small. By relaxing these assumptions, the prediction of section lift of an infinite wing with sweep is generalized to account for a larger variation in airfoil geometry, wing sweep, and flight conditions. The generalized equations derived from the relaxed assumptions are applied to a vortex panel method to obtain section lift predictions for a range of NACA 4-digit airfoils. In an effort to obtain an analytic relationship between the section lift produced by infinite wings with and without sweep, the section lift predictions produced by the vortex panel method are fit to empirical equations. The results are compared to data computed using computational fluid dynamics software.