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Turbulent flow past Generic Space-Shuttle

In this study, computations are performed for turbulent flow past a generic space shuttle configuration. This test case demonstrates the robustness of HiFUN in handling both the geometric complexities and complex flow physics encountered in industrial computations.

Grid Details
S.No
Grid Type
Elements
No of cells (Mn)
1
Unstructured
Body Faces
12,90,9394

Test Conditions

Altitude
Angle of Attack °
Mach Number
Reynolods Number
17,188 m
6.83°
0.9
5.692 million
19,201 m
8.2°
1.31
6.032 million

Results

Surface Streamlines

Flow features like flow separation and flow reattachment can be seen.

Surface Streamlines: M = 0.9
M = 0.9
Surface Streamlines: M = 0.9
M = 0.9
3D Streamlines

Complex flow features like vortices with intense vortical activity can be seen on the wing.

3D streamlines for M = 0.9
3D streamlines for M = 0.9
3D streamlines for M = 0.9
Pressure fill plots

Various complex flow features like bow shock, canopy shock can be seen in the pressure fill plots.

Pressure Fill Plots - M = 0.9
Pressure Fill Plots - M = 1.31

References

www.hobbyspace.com
Frank Garcia,Jr., Karen M. Morrison, Jess H. Jones, Herbert R. Henderson. ``Priliminary sonic boom corelation of predicted and measured levels for STS-1 entry.", NASA-TM-58242, February 1982.

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