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

Shiming Xiao; Zutai Chen

doi:10.1051/matecconf/201817903020

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 journal › Conference article › peer-review

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Abstract

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 language	English
Article number	03020
Number of pages	10
Journal	MATEC Web of Conferences
Volume	179
DOIs	https://doi.org/10.1051/matecconf/201817903020
Publication status	Published - 26 Jul 2018
Externally published	Yes
Event	2018 2nd International Conference on Mechanical, Material and Aerospace Engineering - Wuhan, China Duration: 10 May 2018 → 13 May 2018

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matecconf_2mae2018_03020Final published version, 969 KBLicence: CC BY

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title = "Investigation of flow over the airfoil NACA 0010-35 with various angle of attack",

abstract = " 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. ",

author = "Shiming Xiao and Zutai Chen",

year = "2018",

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doi = "10.1051/matecconf/201817903020",

language = "English",

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journal = "MATEC Web of Conferences",

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T1 - Investigation of flow over the airfoil NACA 0010-35 with various angle of attack

AU - Xiao, Shiming

AU - Chen, Zutai

PY - 2018/7/26

Y1 - 2018/7/26

N2 - 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.

AB - 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.

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DO - 10.1051/matecconf/201817903020

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SN - 2261-236X

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JO - MATEC Web of Conferences

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T2 - 2018 2nd International Conference on Mechanical, Material and Aerospace Engineering

Y2 - 10 May 2018 through 13 May 2018

ER -

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

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