Comparative Numerical Study of NACA0010 and NACA0021 at Various Angles of Attack

7 Pages Posted: 12 Feb 2018

See all articles by Roshmin Suresh

Roshmin Suresh

Indian Institute of Technology, Dhanbad

Abhishek Jain

Indian Institute of Technology, Dhanbad

Date Written: December 21, 2017

Abstract

In present work, an attempt is made to identify the comparative numerical study of NACA0010 and NACA0021 to investigate the coefficient of lift and drag at various angles of attack. The results shown here are for every two degree of angles of attack between 0 o to 10o by computational fluid dynamics analysis. The validations of the present work are done on ANSYS-15(FLUENT) software by comparing the results obtained by UIUC Airfoil coordinate database. It has been observed that the present results are closely matching with the UIUC Airfoil coordinate database. These analyses are done at same Reynolds number (Re) for both NACA0010 and NACA0021. It has been found that NACA0010 shows good characteristics comparatively at different angles of attack under steady flow condition.

Keywords: Airfoil, Lift and Drag, Reynolds Number, Angle of Attack

Suggested Citation

Suresh, Roshmin and Jain, Abhishek, Comparative Numerical Study of NACA0010 and NACA0021 at Various Angles of Attack (December 21, 2017). International Conference on Advances in Thermal Systems, Materials and Design Engineering (ATSMDE2017). Available at SSRN: https://ssrn.com/abstract=3101291 or http://dx.doi.org/10.2139/ssrn.3101291

Roshmin Suresh (Contact Author)

Indian Institute of Technology, Dhanbad ( email )

Sardar Patel Nagar
Dhanbad, Jharkhand 826004
India

Abhishek Jain

Indian Institute of Technology, Dhanbad

Sardar Patel Nagar
Dhanbad, Jharkhand 826004
India

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