This presentation summarises a basic Computational Fluid Dynamics project that analyses aerodynamic flow over a Formula rear wing, and goes on to analyse a slotted rear wing solution, which is commonly used for efficient wing performance.

1. ANALYSIS OF AIR FLOW OVER A FORMULA REAR WING
PROJECT
HEMANTH KUMAR BALASUBRAMANIAN

2. OBJECTIVES
• Study the characteristics of air flow over the rear
wing
• Reduce the drag as much as possible
• Increase the downforce as much as possible
• Improvise

3. ASSUMPTIVE PARAMETERS
• Arbitrary Wing Design
• Non-conformity to any standards
• Mesh quality assumed to be perfect
• Steady State

4. MODEL

5. ZOOMED

6. MESH

7. ZOOMED

8. BOUNDARY CONDITIONS

9. BC & SOLVER OPTIONS LISTED
• Inlet @ 87.5 m/s
• Outlet @ static pressure
• Fluid domain @ 25C
• Wing surface @ 30 C
• Inflated wing surface; free wall fluid domain.
• K-Epsilon model
• Buoyant flow
• Accuracy Order – 1E4
• Iterative limit – 100.

10. SOLVING PROCEDURE
• Multiple iterations with locked boundary conditions
• Variable: Angle of attack
• Parameters of study: Drag force and Downforce.

11. CASCADED DATA GRAPH

12. CASCADED DATA TABLE
Angle of inclination
(Deg)
Drag produced (N) Downforce produced
(N)
35 751.896 1362.13
10 156.151 1722.11
9 157.185 1760.34
8.5 147.53 1780.36
8.4 144.588 1786.15
8.3 141.85 1772.09
6 124.123 1644.5
2 90.9458 1395.98

13. VELOCITY STREAMLINES AT 35 D INCLINATION

14. PRESSURE CONTOUR AT 35 D INCLINATION

15. VELOCITY STREAMLINES AT 2D INCLINATION

16. PRESSURE CONTOUR AT 2D INCLINATION

17. VELOCITY STREAMLINES AT 8.4D INCLINATION

18. PRESSURE CONTOUR AT 8.4D INCLINATION’’

19. SOLUTION PROPOSED
The Dual Element Slotted Rear Wing

20. MODEL

21. MESH

22. VELOCITY STREAMLINES

23. RESULT
• Drag = 7.01039N || 90.9495 N
• Downforce = 3232.19 || 1395.98 N (231.5% ^)

24. PRESSURE CONTOUR

25. THANK YOU
CONTACT: HTTP://WWW.LINKEDIN.COM/IN/HEMANTH-
KUMAR-A7018035