• 한국전산유체공학회:학술대회논문집
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• 2004.10a
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• pp.43-46
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• 2004

Numerical analysis for pressure drag on boattail afterbodies have been studied by Mach number, boattail angle and length ratio of body diameter and base diameter using CFD-FASTRAN that the commercial external flow CFD code. The numerical results have been compared with the experimental data that have been shown pressure drag reduction and supersonic turbulent flow characteristics for boattail afterbodies. And the prediction equation tot boattail base drag has been made by the numerical results about Mach number and boattail configuration parameters.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.7
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• pp.1-8
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• 2005

For study on the unsteady wall interference effect, flows around a circular cylinder in closed test-section wind tunnels have been numerically investigated by solving compressible Navier-Stokes equations. The numerical scheme is based on a node-based finite-volume method with the Roe's flux-difference splitting and an implicit time-integration method coupled with dual time-step sub-iteration. The computed results showed that the unsteady pressure gradient over the cylinder is enhanced by the wall interference, and as a result the fluctuations of lift and drag are augmented. The drag is further increased because of the lower base pressure. The vortex shedding frequency is also increased by the wall interference. The pressure on the test section wall shows the harmonics having the shedding frequency contained in the wall effect.

• Journal of the Society of Naval Architects of Korea
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• v.35 no.3
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• pp.14-25
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• 1998

This paper describes the numerical modelling for the steady and unsteady forces of 3-D wings flying near the free surface based on a potential based panel method. For the steady problem where a wing flies over the fixed float surface, steady lift and drag forces are calculated for wings with and without end-plates having different sections, angle of attacks, aspect patios and flying heights. These numerical results are compared with the wind tunnel test results. The unsteady problem is treated as a boundary value one where a wing flies over the described wavy surface. The unsteady lift force variations of a wing due to different wave lengths and heights are calculated at different flying heights.