Generalized Empirical Airfoil Stagnation Point Location Prediction

Author(s)

Hantae Kang, University of DaytonFollow
Aaron Altman, University of DaytonFollow

Document Type

Article

Publication Date

3-2007

Publication Source

Journal of Aircraft

Abstract

A generalized method for the prediction of a stagnation point location as a function of the angle of attack on symmetrical and cambered wing, and airfoils with varying thickness distribution, is developed using airfoil design software and conformal mapping. The method presents relationship between the stagnation point location a function of the angle of attack, airfoil thickness, degree of camber, and the location of maximum camber.

The conformal mapping method and Designfoil software are used to determine the correlation between Ds, angle of attack and airfoil thickness for symmetrical airfoils. The equation for Ds for the flat plate and the chord normalized x coordinate along with the angle of attack is used to calculate the stagnation point location on the symmetrical airfoil.

Inclusive pages

698-701

ISBN/ISSN

0021-8669

Comments

Permission documentation is on file.

Copyright

Copyright © 2007, American Institute of Aeronautics and Astronautics

Publisher

American Institute of Aeronautics and Astronautics

Volume

44

Issue

2

Peer Reviewed

yes

eCommons Citation

Kang, Hantae and Altman, Aaron, "Generalized Empirical Airfoil Stagnation Point Location Prediction" (2007). Mechanical and Aerospace Engineering Faculty Publications. 124.
https://ecommons.udayton.edu/mee_fac_pub/124