Title

Two Element Linear Strength Vortex Panel Method

Author(s) Information

Clifton A. Cox, California Polytechnic State University, San Luis ObispoFollow

College - Author 1

College of Engineering

Department - Author 1

Aerospace Engineering Department

Degree Name - Author 1

BS in Aerospace Engineering

Date

3-2011

Primary Advisor

Eric Mehiel, College of Engineering, Aerospace Engineering Department

Abstract/Summary

A linear strength vortex panel method was developed to predict the C_p and C_l for a lifting two element airfoil. The linear strength vortex panel method was first validated against thin airfoil theory and experimental data for a single NACA 2412 airfoil. At 2 degrees angle of attack, the linear strength vortex panel method predicted a C_l of about 0.49. Experimental data and thin airfoil theory gave C_l estimations of 0.45 and 0.22 respectively. The Matlab code was then modified to accept a two element airfoil. The two key modifications were the separation of the two different sets of wing element panels and the subsequent addition of a second Kutta condition. The linear strength vortex panel method was then used to determine the C_l and C_p distribution of a two element wing. The two element wing of study was the rear wing airfoil used on the 2008 Formula SAE car. Using a reference length of 1.43 and an angle of attack of 2 degrees, the panel method predicted a C_l of 3.98. Improved results can be obtained by using more panels or better geometry resolution around the leading edge and the gap between the two wing elements.

URL: https://digitalcommons.calpoly.edu/aerosp/28