ANALYSIS OF AIR FLOW OVER A FORMULA REAR WING

PROJECT

HEMANTH KUMAR BALASUBRAMANIAN

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

ASSUMPTIVE PARAMETERS

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

MODEL

ZOOMED

MESH

ZOOMED

BOUNDARY CONDITIONS

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.

SOLVING PROCEDURE

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

CASCADED DATA GRAPH

CASCADED DATA TABLE

Angle of inclination (Deg)

Drag produced (N) Downforce produced (N)

35 751.896 1362.1310 156.151 1722.119 157.185 1760.348.5 147.53 1780.368.4 144.588 1786.158.3 141.85 1772.096 124.123 1644.52 90.9458 1395.98

VELOCITY STREAMLINES AT 35 D INCLINATION

PRESSURE CONTOUR AT 35 D INCLINATION

VELOCITY STREAMLINES AT 2D INCLINATION

PRESSURE CONTOUR AT 2D INCLINATION

VELOCITY STREAMLINES AT 8.4D INCLINATION

PRESSURE CONTOUR AT 8.4D INCLINATION’’

SOLUTION PROPOSED

The Dual Element Slotted Rear Wing

MODEL

MESH

VELOCITY STREAMLINES

RESULT

• Drag = 7.01039N || 90.9495 N

• Downforce = 3232.19 || 1395.98 N (231.5% ^)

PRESSURE CONTOUR

THANK YOU

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