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Supersonic inviscid flow past monoplanar missile configuration

In this study, computations are performed for supersonic inviscid flow past a monoplanar missile [1] configuration. This configuration has a body consisting of ogive-cylinder, two wings and four fins arranged in cruciform position.

Grid Details

Grid
Mach fill plot
S.No
Grid Type
Elements
No of cells (Mn)
1
Unstructured
Tetrahedra
1100949

Test Conditions

Altitude
Angle of Attack (°)
Mach Number (°)
Reynolds Number (Mn/Mtr)
-
8°
2.16
-

Results

The drag polar obtained using HiFUN compares well with the experimental results.
Drag polar

References

Blair A. B. Jr.,``Stability and control characteristics of a monoplanar missile configuration with two low-profile tail arrangements at Mach numbers from 1.70 to 2.86", NASA TM X-3533, Langley Research Center, August, 1977.

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