Flow Simulation over an Airfoil for varying Angle of Attack using SolidWorks
Aim: To model and simulate the flow over a NACA0017 airfoil.
Objective: To compare the lift and drag forces for the angle of attacks 0,2,4,6,8,10 degrees.
Introduction:
This assignment consists of a flow simulation over NACA 0017 Airfoil at different angles of attack. An Airfoil is a structure with curved surfaces designed to give the most favorable ratio of lift to drag in flight. The main applications of an airfoil are in most aircraft as a basic form of the wings, fins, and horizontal stabilizers.
Terminologies of an airfoil:
[1]
The lift produced by an airfoil is the net force produced perpendicular to the relative wind. The drag incurred by an airfoil is the net force produced parallel to the relative wind [1].
The angle of attack plays a definitive role in generating the Lift and the Drag Forces. This study primarily focuses on the variation in the Drag and Lift forces caused due to change in the angle of attack.
Problem Specification:
- Geometry: NACA 0017 Airfoil
- Airfoil coordinate data file: Click Here [2]
- Relative Wind/Velocity: 600 m/s
- Type of Analysis: 2D, External, Transient Flow
- Fluid: Air
- Viscosity: 1.81e-5 Pa-s
- Density: 1.225 kg/m^3
- Computational Domain: -5m to 15m in the X direction, -5m to 5m in the Y direction
- Start time: 0s
- End Time: 5s
- Time step: 1s
- Pressure: 1 atm (101325 Pa)
- Representation of Drag Force in Results: SG Force (X) 1
- Representation of Lift Force in Results: SG Force (Y) 1
Results:
- Angle of Attack = 0 deg:
Velocity Plot:
Convergence Plot of Drag Force:
Convergence Plot of Lift Force:
Lift and Drag Force Table:
- Angle of Attack = 2 deg:
Velocity Plot:
Convergence Plot of Drag Force:
Convergence Plot of Lift Force:
Lift and Drag Force Table:
- Angle of Attack = 4 deg:
Velocity Plot:
Convergence Plot of Drag Force:
Convergence Plot of Lift Force:
Lift and Drag Force Table:
- Angle of Attack = 6 deg:
Velocity Plot:
Convergence Plot of Drag Force:
Convergence Plot of Lift Force:
Lift and Drag Force Table:
- Angle of Attack = 8 deg:
Velocity Plot:
Convergence Plot of Drag Force:
Convergence Plot of Lift Force:
Lift and Drag Force Table:
- Angle of Attack = 10 deg:
Velocity Plot:
Convergence Plot of Drag Force:
Convergence Plot of Lift Force:
Lift and Drag Force Table:
Variation of Lift and Drag Force with respect to the Angle of Attack:
Table for Drag and Lift Forces (Average Values):
Plot of Drag Force vs Angle of Attack:
Plot of Lift Force vs Angle of Attack:
Conclusion:
The Drag Force varies non-linearly as we increase the Angle of Attack whereas the Lift Force shows a linear variation with an increase in the Angle of Attack.
The maximum Drag Force value is lower than the maximum Lift Force when the angle of attack is 10 degrees. On the other hand, the minimum Drag Force value is higher than the minimum Lift Force value at 2 degrees of the Angle of Attack. This indicates that there is a larger variation in the Lift Force as compared to the Drag Force with an increase in the Attack Angle.
References:
[1] Angle of Attack, http://www.aviationchief.com/angle-of-attack.html
[2] Airfoil Tools, NACA 4 digit airfoil generator (NACA 0017 AIRFOIL), http://airfoiltools.com/airfoil/naca4digit?MNaca4DigitForm%5Bcamber%5D=0&MNaca4DigitForm%5Bposition%5D=0&MNaca4DigitForm%5Bthick%5D=17&MNaca4DigitForm%5BnumPoints%5D=81&MNaca4DigitForm%5BcosSpace%5D=0&MNaca4DigitForm%5BcosSpace%5D=1&MNaca4DigitForm%5BcloseTe%5D=0&yt0=Plot