Hostname: page-component-cd9895bd7-jn8rn Total loading time: 0 Render date: 2025-01-03T02:11:24.987Z Has data issue: false hasContentIssue false
  • English
  • Français

Numerical simulation of the vortex-fin interaction over a tangent-ogive cylinder

Published online by Cambridge University Press:  04 July 2016

A.A. Omar ,
K. Chongam  and
R. Oh-Hyun
A.A. Omar
Affiliation:
Department of Aerospace Engineering, University Putra Malaysia, Serdang, Malaysia
K. Chongam
Affiliation:
Department of Aerospace Engineering, Seoul National University, Seoul, Korea
R. Oh-Hyun
Affiliation:
Department of Aerospace Engineering, Seoul National University, Seoul, Korea
Get access Rights & Permissions [Opens in a new window]

Abstract

The interaction between slender body vortices and a single vertical fin located down the axis of the body is investigated numerically for angle of attack of 30 deg and Reynolds number of 6000. The present research includes a parametric study on the effect of fin location and fin azimuthal position. A numerical method based on the pseudo-compressibility is used for solving the three-dimensional incompressible Navier-Stokes equations using the Lower-Upper Symmetric Gauss-Seidel implicit scheme. The numerical results show that the vortices remain very coherent and attached to the body until they reach the fin section, where they become less coherent and begin to separate from the body. Also, the results show that the fin location does not affect the upstream development of the vortices, but it does affect the location at which the vortices separate from the body. The effect of azimuthal fin positions was also investigated. As the azimuthal angle of the fin increased, the size of the vortex on the port side decreased, but the starboard side vortex grew in size and moved across the leeward ray to the port side. The computed results are found to agree well with the available experimental data. The effect of the grid size on the numerical solutions was also investigated.

Type
Research Article
Information
The Aeronautical Journal , Volume 106 , Issue 1058 , April 2002 , pp. 175 - 184
Copyright
Copyright © Royal Aeronautical Society 2002 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Acharya, M., Kiedaisch, J. and Hassan, M. M. Asymmetric vortical flows over slender bodies with appendages, IIT Fluid Dynamics Research Center, TR, Chicago, IL, Jun 1994.Google Scholar
2. Hwang, S. J. and Rho, O. H. Lower-upper symmetric gauss-seidel scheme exhibiting asymmetric vortices over slender bodies, 1996, J Spacecr and Rockets, 33, (3), pp 750–752.Google Scholar
3. Hartwich, P. M. and Hall, R. M. Navier-Stokes solutions for vortical flows over a tangent-ogive cylinder, 1990, AIAA J, 28, (7), pp 1171–1179.Google Scholar
4. Chan, N. Q., Wang, Z. W. and Huang, Z. Asymmetric vortices and alleviation on the slender bodies with and without wings, 1997, AIAA Paper 97-0748.Google Scholar
5. Zilliac, G. G. Computational/experimental study of the flow field on a body of revolution at incidence, 1989, AIAA J, 27, (8), pp 1008–1016.Google Scholar
6. Wardlaw, A. B. and Yanta, J. Asymmetric flowfield development on a slender body at high incidence, 1984, AIAA J, 22, (2), pp 242–249.Google Scholar
7. Nielson, J. N. Missile aerodynamics-past, present, future, 1980, J Spacecr Rockets, 17, (3), pp 165–175.Google Scholar
8. Kiedaisch, J. W. and Acharya, M. Interaction of missile nose-tip vortices with a control surface, 1996, AIAA J, 34, (5), pp 999–1006.Google Scholar
10. Mendenhall, M. and Perkins, S. Vortex induced characteristics of missiles in unsteady maneuvers, 1989, AIAA Paper 89-0344.Google Scholar
11. Kandil, O.A., Sheta, E.F. and Massey, S.J. Twin tail/delta wing configuration buffet due to unsteady vortex breakdown flow, 1996, AIAA Paper 96-2517.Google Scholar
12. G.A., Johnson Overall forces and moments on wing-bodies at high incidence, 1988, AIAA Paper 88-4354.Google Scholar
13. Canbazoglu, S., Lin, J.C., Wolfe, S. and Rockwell, D. Buffeting of a fin: streamwise evolution of flow structure, 1995, J Aircr, 33, (1), pp 185–190.Google Scholar
14. Meyer, J. Effect of the roll angle on cruciform wing-body configurations at high incidences, 1994, J Spacecr Rockets, 31, (1), pp 113–122.Google Scholar
15. Washburn, A.E., Jenkins, L.N. and Ferman, M.A. Experimental investigation of vortex-fin interaction, 1993, AIAA Paper 93-0050.Google Scholar
16. Rizk, Y.M. and Gee, K. Unsteady simulation of flowfield around F-18 aircraft at large incidence, 1992, J of Aircr, 29, (6).Google Scholar
17. Rizzeta, D.P. Numerical simulation of the interaction between a leading-edge vortex and a vertical tail, 1996, AIAA Paper 96-2012.Google Scholar
18. Degani, D. Effect of geometrical disturbance on vortex asymmetry, 1991, AIAA J, 29, (4), pp 560–565.Google Scholar
19. Ok, H.N. Development of an Incompressible Navier-Stokes Solver and its Applications to the Calculation of Separated Flows, 1993, Ph.D Dissertation, Department of Aeronautics and Astronautics, University of Washington.Google Scholar
20. Rogers, S.E. and Kwak, D.H. Upwind differencing scheme for the time-accurate incompressible Navier Stokes equations, 1990, AIAA J, 28, (2), pp 253–262.Google Scholar
21. Rogers, S.E., Kwak, D.H. and Kiris, C. Steady and unsteady solutions of the incompressible Navier Stokes equations, 1991, AIAA J, 29, (4), pp 603–610.Google Scholar
22. Yoon, S.K. and Kwak, D.H. Three-dimensional incompressible Navier-Stokes solver using lower-upper symmetric-Gauss-Seidel algorithm, 1991, AIAA J, 29, (6), pp 874–875.Google Scholar
23. Kwak, D.H. and Chakravarthy, S.R. A three-dimensional incompressible Navier-Stokes solver using primitive variables, 1986, AIAA J, 24, (3), pp 390–396.Google Scholar
24. Visbal, M.R. Computed unsteady structure of spiral vortex breakdown on delta wings, AIAA 96-2074, New Orleans, Jun 1996.Google Scholar