Validation of the flow field around DARPA SUBOFF model

Authors: A. Cimpoeru (CFMS), J. Appa (Zenotech) and D. Standingford (Zenotech)

December 2014

Abstract

In this section the flow field around DARPA SUBOFF geometry is computed using the unstructured cell centered finite volume density based solver zCFD. For this study the AFF8 configuration was employed due to complex flow features such as boundary layer - vortex and vortex-vortex interactions. The Reynolds number for this test case is \(Re=1.2e07\) and the employed turbulence model is k-ω SST. The steady state solutions are validated against wind tunnel data (see Reference) and have shown agreement.

Configuration (Axisymmetric hull + Fairwater + Stern appendages )

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SUBOFF Configuration

Results

Steady state RANS, SOLAR - octree mesh (14 and 30 M cells), \(Mach=0.0179\), \(Re=1.2e7\) (model length based)

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Coefficient of pressure in the symmetry plane

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Coefficient of pressure contours

Wake development ( Left – Coarse Mesh ; Right – Fine Mesh )

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x/L = 0.3

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x/L = 0.4

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x/L = 0.5

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x/L = 0.978 (Propeller Plane)

Comparison against zCFD, experimental data and Bhushan et al (2013) (FLUENT)

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x/L = 0.978 (Propeller Plane)

See also

Summary of DARPA Suboff Experimental program data

Geometric Characteristics of DARPA SUBOFF models

‘S. Bhushan, M. F. Alam and D. K. Walters. Evaluation of hybrid RANS/LES models for prediction of flow around surface combatant and Suboff geometries. Computer and Fluids 88 (2013) 834-849’

DARPA SUBOFF Notebook