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Turbulent supersonic flow past ELAC-1

In this study, computations are performed for supersonic turbulent flow past ELAC-1 (Elliptic Aerodynamic configuration) configuration. This aerospace vehicle consisting of a delta wing with a sweep angle of 75 degrees and stabilizer fins at the wing tips.

Grid Details

ELAC Domains
ELAC Grid 1
S.No
Grid Type
Elements
No of cells (Mn)

Test Conditions

Altitude
Angle of Attack (°)
Mach Number (°)
Reynolds Number (Mn/Mtr)

Results

Cp Distrubution Comparison

There is an excellent comparison of computed Pressure distribution at different angles of attack with the experimental numbers.

alpha = 0°
alpha = 0°
alpha = 3°
alpha = 3°
alpha = 6°
alpha = 6°
alpha = 10°
alpha = 10°
Streamline Plots

Complex flow features like Flow separation, Flow reattachment, vortices with intense vortical activity are seen in the streamline plots.

Surface Streamlines: alpha = 6°
Surface Streamlines: alpha = 6°
Surface Streamlines: alpha = 10°
Surface Streamlines: alpha = 10°
3D Streamlines
3D Streamlines
3D Streamlines at Winglet
3D Streamlines at Winglet

References

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