Investigation of flow over the airfoil NACA 0010-35 with various angle of attack

Shiming Xiao*, Zutai Chen

*Corresponding author for this work

Research output: Contribution to journalConference articlepeer-review

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This report is using the finite element analysis method to investigate the performance of an airfoil (NACA 0100-35), which uses 2D computational fluid dynamics simulations based on ANSYS to find the lift and drag coefficients under different conditions. The boundary conditions are defined as follows: The density is 1kg/m 3 , gauge pressure is 0, and airflow velocity is 50m/s. Also the Reynolds number is considered during the simulation. As a result, the simulation shows the stalling points and efficiencies of the airfoil under different angles of attack. The simulation also plots the contours and stream lines in these conditions.

Original languageEnglish
Article number03020
Number of pages10
JournalMATEC Web of Conferences
Publication statusPublished - 26 Jul 2018
Externally publishedYes
Event2018 2nd International Conference on Mechanical, Material and Aerospace Engineering - Wuhan, China
Duration: 10 May 201813 May 2018


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