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Supersonic turbulent flow past M910 spinning projectile

In this study, supersonic turbulent computations are performed for M910 spinning projectile. This projectile is a target practice, discarding sabot–traced (TPDS–T) projectile. Computations are performed for a wide range of supersonic Mach numbers.

Grid Details

Structured Multiblock grid
Structured Multiblock grid
Structured Multiblock grid
S.No
Grid Type
Elements
No of cells (Mn)
1
Subsonic
28,440
3,39,1860
2
Supersonic
28,440
2,40,4860

Test Conditions

Angle of Attack (°)
Mach Number (°)
Spin rate (rad/sec)
ReD (million)
0.0
0.5
1789
0.1895
0.0
0.9
3220
0.3402
0.0
1.02
3649
0.3855
0.0
2.5
8944
0.9444
0.0
4.5
16100
1.701

Results

Mach Fill Plots

The flow features like shocks, expansion fans, wakes can be seen at different Mach numbers.

M = 0.5
M = 0.5
M = 0.9
M = 0.9
M = 1.02
M = 1.02
M = 2.5
M = 2.5
M = 4.5
M = 4.5
Drag Coefficient Comparison

An excellent comparison of computed drag coefficient can be seen with the experimental results.

References

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