Hostname: page-component-7bb8b95d7b-2h6rp Total loading time: 0 Render date: 2024-09-14T08:55:12.277Z Has data issue: false hasContentIssue false
  • English
  • Français

Numerical simulation of the flow field over conical, disc and flat spiked body at Mach 6

Published online by Cambridge University Press:  03 February 2016

R. C. Mehta
R. C. Mehta*
Affiliation:
drrakhab.mehta@gmail.com, Nanyang Technological University, Singapore
Get access Rights & Permissions [Opens in a new window]

Abstract

A forward facing spike attached to a hemispherical body significantly changes its flow field and influences aerodynamic drag and wall heat flux in a high speed flow. The dynamic pressure in the recirculation area is highly reduced and this leads to the decrease in the aerodynamic drag and heat load on the surface. Consequently, the geometry, that is, the length and shape of the spike, has to be simulated in order to obtain a large conical recirculation region in front of the blunt body to get beneficial drag reduction. It is, therefore, a potential candidate for aerodynamic drag reduction for a future high speed vehicle. Axisymmetric compressible laminar Navier-Stokes equations are solved using a finite volume discretisation in conjunction with a multistage Runge-Kutta time stepping scheme. The effect of the spike length and shape, and the spike nose configuration on the reduction of drag is numerically evaluated at Mach 6 at a zero angle-of-attack. The computed density contours agree well with the schlieren images. Additional modification to the tip of the spike to get different types of flow field such as the formation of a shock wave, separation area and reattachment point are examined. The spike geometries include the conical spike, the flat-disk spike and the hemispherical disk spike of different length to diameter ratios attached to the blunt body.

Type
Research Article
Information
The Aeronautical Journal , Volume 114 , Issue 1154 , April 2010 , pp. 225 - 236
Copyright
Copyright © Royal Aeronautical Society 2010 

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. Riggins, D., Nelson, H.F. and Johnson, E., Blunt body wave drag reduction using focused energy deposition, AIAA J, 1999, 27, pp 460–467.Google Scholar
2. Kobayashi, H., Maru, Y. and Fukiba, K., Experimental study on aerodynamic characteristics of telescopic aerospikes with multiple disks, J Spacecraft and Rockets, 2007, 44, (1), pp 33–41.Google Scholar
3. Bogdonoff, S.M. and Vas, I.E., Preliminary investigations of spike bodies at hypersonic speeds, J Aerospace Sciences, February 1959, 26, (2), pp 65–74.Google Scholar
4. Maull, D.J., Hypersonic flow over symmetric spiked bodies, J Fluid Mechanics, 1960, 8, (584).Google Scholar
5. Wood, C.J.. Hypersonic flow over spiked cones, J Fluid Mechanics, 1961, 12, (614).Google Scholar
6. Menezes, V., Saravanan, S., Jagdeesh, G. and Reddy, K.P., Experimental investigation of hypersonic flow over highly blunted cones with aerospikes, AIAA J, 2003, 41, (10), pp 1955–1966.Google Scholar
7. Mehta, R.C., Pressure oscillations over a spiked blunt body at hypersonic Mach number, Computational Fluid Dynamics J, July 2000, 9, (2), pp 88–95.Google Scholar
8. Mehta, R.C., Numerical analysis of pressure oscillations over axisym-metric spiked blunt bodies at Mach 6·8, Shock Waves, 2002, 11, pp 431–440.Google Scholar
9. Milicv, S.S., Pavlovic, M.D., Ristic, S. and Vitic, A., On the influence of spike shape at supersonic flow past blunt bodies, Faculty Universities, Series: Mechanics, Automatic Control and Robotic, 2002, 3, (12), pp 371–382.Google Scholar
10. Caarese, W. and Hankey, W.L., Modes of shock wave oscillations on spike tipped bodies, AIAA J, 23, (2), 1985, pp 185–192.Google Scholar
11. Hahn, M., Pressure distribution and mass injection effects in the transitional separated flow over a spiked body at supersonic speed, J Fluid Mechanics, February 1966, 24, part 2, pp 209–223.Google Scholar
12. Milicev, S.S. and Pavlovic, M.D., Influence of spike shape at supersonic flow past blunt nosed bodies experimental study, AIAA J, 2002, 40, (5), pp 1018–1020.Google Scholar
13. Kubota, H., Some aerodynamic and aerothermodynamic considerations for reusable launch vehicles, AIAA-2004-2428.Google Scholar
14. Crawford, D.H., Investigation of the flow over a spiked-nose hemisphere at a Mach number of 6·8, NASA TN-D 118, December 1959.Google Scholar
15. Motoyama, N., Mihara, K., Miyajima, R., Watanuki, W. and Kubota, H., Thermal protection and drag reduction with use of spike in hypersonic flow, AIAA Paper 2001-1828, 2001.Google Scholar
16. Yamauchi, M., Fujjii, K., Tamura, Y. and Higashino, F., Numerical investigation of hypersonic flow around a spiked blunt body, AIAA paper 93-0887, January 1993.Google Scholar
17. Shoemaker, J.M., Aerodynamic spike flowfields computed to select optimum configuration at Mach 2·5 with experimental validation, AIAA Paper 90-0414, 1990.Google Scholar
18. Fujita, M. and Kubota, H., Numerical simulation of flowfield over a spiked blunt nose, Computational Fluid Dynamics J, 1992, 1, (2), pp 187–195.Google Scholar
19. Boyce, R., Neely, A., Odam, J. and Stewart, B., CFD Analysis of the HyCAUSE Nose-Cone, AIAA Paper 2005-3339, May 2005.Google Scholar
20. Milicev, S.S., Pavlovic, M.D., Ristic, S. and Vitic, A., On the influence of spike shape at supersonic flow past blunt bodies, Mechanics, Automatic Control and Robotics, 2002, 3, (12), pp 371–382.Google Scholar
21. Mehta, R.C., Peak heating for reattachment of separated flow on a spiked blunt body, Heat and Mass Transfer, 2000, 36, pp 277–283.Google Scholar
22. Mehta, R.C. and Jayachandran, T., Navier-Stokes solution for a heat shield with and without a forward facing spike, Computers and Fluids, 1997, 26, (7), pp 741–754.Google Scholar
23. Mehta, R.C., Heat transfer study of high speed over a spiked blunt body, Int J Numerical Methods for Heat & Fluid Flow, 2000, 10, (7), pp 750 – 769.Google Scholar
24. Gauer, M. and Paull, A., Numerical investigation of a spiked nose cone at hypersonic speeds, J Spacecraft and Rockets, 2008, 45, (3), pp 459–471.Google Scholar
25. Peyret, R. and Vivind, H., Computational Methods for Fluid Flows, Springer-Verlag, 1993, Berlin, Germany, pp 109–111.Google Scholar
26. Jameson, A., Schmidt, W. and Turkel, E., Numerical simulation of Euler equations by finite volume methods using Runge-Kutta Time Stepping Schemes, AIAA paper 81-1259, June 1981.Google Scholar
27. Mehta, R.C., Numerical investigation of viscous flow over a hemisphere-cylinder, Acta Mechanica, 1998, 128, (1-2), pp 48–58.Google Scholar
28. Shang, J.S., Numerical simulation of wing-fuselage aerodynamic interference, AIAA J, 1984, 22, (10), pp 1345–1353.Google Scholar
29. Mehta, R.C., A quasi-three dimensional automatic grid generation method, in the proceedings of the 25th National & International Conference on Fluid Dynamics & Fluid Power, Indian Institute of Technology, Delhi, India, December 1998, pp 89–98.Google Scholar
30. Mehta, R.C., Numerical heat transfer study over spiked-blunt body at Mach 6.8, AIAA Paper 2000-0344, January 2000 and also J Spacecraft & Rockets, 2000, 37, (5), pp 700 – 701.Google Scholar
31. Truitt, R.W., Hypersonic Aerodynamic, The Ronald Press Co, New York, USA, 1959.Google Scholar
32. Liepmann, H.W. and Roshko, A., Elements of Gas Dynamics, 2007, Dover Publications Inc, First South Asian Edition, New Delhi, India.Google Scholar
33. Mair, W.A., Experiments on separation on boundary layers on probes in front of blunt bodies at supersonic air stream, Philosophical Magazine, 1952, 43, pp 695–716.Google Scholar
34. Kalimuthu, R., Mehta, R.C. and Rathakrishnan, E., Experimental Investigation on spiked body in hypersonic flow, Aeronaut J, October 2008, 112, (1136), pp 593–598.Google Scholar
35. Kalimuthu, R., Mehta, R.C. and Rathakrishnan, E., Blunt body drag reduction using aero-spike and aero-disk at Mach 6, in the proceedings of International Conference on High Speed Trans-atmospheric Air & Space Transportation, Hyderabad, India, June 2007, pp 178–188.Google Scholar