Numerical Simulation of NACA 2415 Airfoil at Different Low Reynolds Numbers and Angles of Attack

Aakash Srivastava; Vatsalya Tiwari; Raj Kumar Singh

doi:https://doi.org/10.51976/ijari.441622

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Numerical Simulation of NACA 2415 Airfoil at Different Low Reynolds Numbers and Angles of Attack

Aakash Srivastava , Vatsalya Tiwari, Raj Kumar Singh

Vol 4 , Issue 4 , October - December 2016 | Pages: 127-133 | Research Paper

https://doi.org/10.51976/ijari.441622

Received: September 20, 2016 | Revised: October 20, 2016 | Accepted: November 28, 2016 | Published Online: December 15, 2016

Author Details ( * ) denotes Corresponding author

1. Aakash Srivastava Department of Mechanical Engineering, Delhi Technological University, Bawana Road, Delhi,

2. Vatsalya Tiwari, Department of Mechanical Engineering, Delhi Technological University, Bawana Road, Delhi, (atsalya.tiwari.vns@gmail.com)

3. Raj Kumar Singh, Department of Mechanical Engineering, Delhi Technological University, Bawana Road, Delhi, (rksingh.dtu@gmail.com)

This project simulates NACA2415 airfoil on ANSYS Workbench and ANSYS FLUENT at low Reynolds numbers at different angles of attack. This is a 2-D simulation andSpalart-Allmaras is the preferred turbulentmodel solver for this process, it yielded more results closer to experimental results when compared against K-epsilon and other turbulent models.Contours of Pressure and Velocity are presented in this paper with their inferences discussed while Plots of Coefficient of Pressure (CP) about the chord lengths along the airfoil and Coefficient of Lift (CL) are plotted to compare the CFD and the experimental results. Effect of Reynolds number and Angle of Attack is thus studied and investigated.

Keywords

Computational Fluid Dynamics (CFD); NACA2415; FLUENT; Spalart-Allmaras; Validation of Results Effect of Reynolds Number and Angle of Attack.

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