Matsson, J. E., & Voth, J. A., & McCain, C. A., & McGraw, C. (2016, June), Aerodynamic Performance of the NACA 2412 Airfoil  at Low Reynolds Number  Paper presented at 2016 ASEE Annual Conference & Exposition, New Orleans, Louisiana. 10.18260/p.26539

\bibitem{asee_peer_26539}
  Matsson, J. E., \& Voth, J. A., \& McCain, C. A., \& McGraw, C. (2016, June), \emph{Aerodynamic Performance of the NACA 2412 Airfoil  at Low Reynolds Number}
  Paper presented at 2016 ASEE Annual Conference \& Exposition, New Orleans, Louisiana.
  10.18260/p.26539

John E Matsson, John A. Voth, Connor A. McCain, and Connor McGraw.  "Aerodynamic Performance of the NACA 2412 Airfoil  at Low Reynolds Number".  2016 ASEE Annual Conference & Exposition, New Orleans, Louisiana, 2016, June.  ASEE Conferences, 2016.  https://peer.asee.org/26539 Internet.  26 Apr, 2024

\bibitem{asee_peer_26539}
  John E Matsson, John A. Voth, Connor A. McCain, and Connor McGraw.
  "Aerodynamic Performance of the NACA 2412 Airfoil  at Low Reynolds Number".
  \emph{2016 ASEE Annual Conference \& Exposition, New Orleans, Louisiana, 2016, June}.
  ASEE Conferences, 2016.
  https://peer.asee.org/26539 Internet.  26 Apr, 2024

@INPROCEEDINGS{asee_peer_26539
author = "John E Matsson, John A. Voth, Connor A. McCain, and Connor McGraw"
title = "Aerodynamic Performance of the NACA 2412 Airfoil  at Low Reynolds Number"
booktitle = "2016 ASEE Annual Conference \& Exposition"
year = "2016"
month = "June"
address = "New Orleans, Louisiana"
publisher = "ASEE Conferences"
note = {https://peer.asee.org/26539}
number = {10.18260/p.26539}
}

TY  - CPAPER
AB  - This paper shows a project by three honors students in an undergraduate engineering program. Students used a 3D printer to fabricate the NACA 2412 wing section with a chord length of 230 mm and a total assembled span of 305 mm. The wing was printed in three hollow sections including a 25 mm wide inner section that included 36 surface holes with attached brass tubes and Tygon tubing for pressure distribution measurements in the wind tunnel. The outer sections were 140 mm wide and assembled on each side of the inner section. LabVIEW software and a stepper motor were used for measurements and automatic control of the angle of attack. A Scanivalve Solenoid Controller with Pulser connected to two Fluid Switch Wafers was used for scanning of the pressure field. The experiments were compared with CFD simulations using ANSYS Fluent software at Reynolds number 200,000 based on free stream velocity and chord length. Detailed descriptions of the experimental design, fabrication, set-up and cost are included in the paper together with a tutorial on the details of the mesh generation and settings for the CFD simulations. Finally, the paper will provide details of outcomes for the project, faculty observations, student involvement and response, and assessment of student work.

AU  - John E Matsson
AU  - John A. Voth
AU  - Connor A. McCain
AU  - Connor McGraw
CY  - New Orleans, Louisiana
DA  - 2016/06/26
PB  - ASEE Conferences
TI  - Aerodynamic Performance of the NACA 2412 Airfoil  at Low Reynolds Number
UR  - https://peer.asee.org/26539
DO  - 10.18260/p.26539
ER  -