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Investigation of aerodynamic coefficients at Mach 6 over conical, hemispherical and flat-face spiked body

  • R. Kalimuthu (a1), R. C. Mehta (a2) and E. Rathakrishnan (a3)

Abstract

A forward spike attached to a blunt body significantly alters its flow field characteristics and influences aerodynamic characteristics at hypersonic flow due to formation of separated flow and re-circulation region around the spiked body. An experimental investigation was performed to measure aerodynamic forces for spikes blunt bodies with a conical, hemispherical and flat-face spike at Mach 6 and at an angle-of-attack range from 0° to 8° and length-to-diameter L/D ratio of spike varies from 0.5 to 2.0, where L is the length of the spike and D is diameter of blunt body. The shape of the leading edge of the spiked blunt body reveals different types of flow field features in the formation of a shock wave, shear layer, flow separation, re-circulation region and re-attachment shock. They are analysed with the help of schlieren pictures. The shock distance ahead of the hemisphere and the flat-face spike is compared with the analytical solution and is showing satisfactory agreement with the schlieren pictures. The influence of geometrical parameters of the spike, the shape of the spike tip and angle-of-attack on the aerodynamic coefficients are investigated by measuring aerodynamic forces in a hypersonic wind tunnel. It is found that a maximum reduction of drag of about 77% was found for hemisphere spike of L/D = 2.0 at zero angle-of-attack. Consideration for compensation of increased pitching moment is required to stabilise the aerodynamic forces.

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1. Hillji, E.R. and Nelson, R.L. Ascent air data system results from the space shuttle flight test program, NASA Langley Research Center, 8-10 March 1983, Hampton, VA, US, NASA CR 2283.
2. Mehta, R.C. and Jayachandran, T. Navier-Stokes solutions for a heat shield with and without forward facing spikes, Computers & Fluids, 1997, 26, (1), pp 741-754.
3. Mikhail, A.G. Spiked-nosed projectiles: Computations and dual flow modes in supersonic flight, J Spacecraft and Rockets, 1991, 28, (4), pp 418-424.
4. d'Humieres, G. and Stollery, J.L. Drag reduction on a spiked body at hypersonic speed, Aeronautical J, Feb. 2010, 114, (1152), pp 113-119.
5. Crawford, D.H. Investigation of the flow over a spiked-nose hemisphere at a mach number of 6.8, NASA TN-D 118, 1959.
6. Bogdonoff, S.M. and Vas, I.E. Preliminary investigations of spike bodies at hypersonic speeds, J Aerospace Sciences, 1959, 26, (2), pp 65-74.
7. Maull, D.J. Hypersonic flow over symmetric spiked bodies, J Fluid Mechanics, 1960, 8, pp 584-592.
8. Wood, C.J. Hypersonic flow over spiked cones, J Fluid Mechanics, 1962, 12, pp 614-624.
9. Chang, P.L. Separation of Flow, 1970, Pergamon Press, Oxford, UK, pp 469-525.
10. Kubota, H. Some aerodynamic and aerothermodynamic considerations for reusable launch vehicles, 34th AIAA Fluid Dynamics Conference and Exhibit, Fluid Dynamics, 28 June-1 July, 2004, Portland, Oregon, US, 2004, 2428.
11. Motoyama, N., Mihara, K., Miyajima, R., Watanuki, W. and Kubota, H. Thermal protection and drag reduction with use of spike in hypersonic flow, 10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies, Kyoto, Japan, AIAA Paper 2001-1828, 2001. Available at: https://arc.aiaa.org/doi/abs/10.2514/6.2001-1828.
12. 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, 2001, 3, (12), pp 371-382.
13. Menezes, V., Saravanan, S., Jagadeesh, G. and Reddy, K.P.J. Experimental investigations of hypersonic flow over highly blunted cones with aerospikes, AIAA J, 2003, 41, (10), pp 1955-1966.
14. Kalimuthu, R., Mehta, R.C. and Rathakrishnan, E. Experimental investigation on spiked body in hypersonic flow, Aeronautical J, 2008, 112, (1136), pp 593-598.
15. Yamauchi, M., Fujjii, K., Tamura, Y. and Higashino, F. Numerical investigation of hypersonic flow around a spiked blunt body, AIAA 31st Aerospace Sciences Meeting, 11-14 January 1984, Reno, NV, US, AIAA paper 93-0887.
16. Mehta, R.C. Numerical simulation of the flow field over conical, disc and flat spiked body at Mach 6, The Aeronautical J, 2010, 114, (1154), pp 225-236.
17. Shoemaker, J.M. Aerodynamic spike flowfields computed to select optimum configuration at Mach 2.5 with experimental validation, 28th Aerospace Science Meeting, 8-11 January 1990, Reno, NV, US, AIAA Paper 90-0414.
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.
19. Gerdroodbary, M.B. and Hosseinalipour, , S.M. Numerical simulation of hypersonic flow over highly blunted cones with spike, Acta Astronutica, 2010, 67, pp 180-193.
20. Mehta, R.C. Numerical analysis of pressure oscillations over axisymmetric spiked blunt bodies at Mach 6.8, Shock Waves, 2002, 11, pp 43-440.
21. 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.
22. Ahmed, M.Y.M. and Qin, A. Drag reduction using aerodiscs for hypersonic hemispherical bodies, J Spacecraft and Rockets, 2010, 47, (1), pp 62-80.
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.
24. Ahmed, M.Y.M. and Qin, N. Recent advances in the aerothermodynamics of spiked hypersonic vehicles, Progress in Aerospace Sciences, 2011, 47, (6), pp 425-449.
25. Kalimuthu, R., Mehta, R.C. and Rathakrishnan, E. Pressure measurements over a hemisphere-cylinder body attached with a forward facing spike, Aeronautical J, June 2013, 117, (1192), pp 639-646.
26. Liepmann, H.W. and Roshko, A. Elements of Gas Dynamics, 1st South Asian Edition, 2007, Dover Publications Inc., New Delhi, India.
27. Truitt, R.W. Hypersonic Aerodynamic, 1959, Ronald Press Co., New York, New York, US.
28. Hayer, W.D. and Probstein, R.F. Hypersonic Flow Theory, 1959, Academic Press, New York, New York, US.
29. Probstein, R.F. Inviscid flow in the stagnation region of very blunt-nosed bodies at hypersonic flight speeds, September 1956, U.S. Air Force, Washington, DC, WADC TN 56-395.
30. Ames Research Staff. Equations, tables and charts for compressible flow, 1953, Moffett Field, CA, US, NACA report 1135.
31. Mehta, R.C. Numerical heat transfer study around a spiked blunt-nose body at Mach 6, Heat and Mass Transfer (Springer), April 2013, 49, (4), pp 485-496.

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Investigation of aerodynamic coefficients at Mach 6 over conical, hemispherical and flat-face spiked body

  • R. Kalimuthu (a1), R. C. Mehta (a2) and E. Rathakrishnan (a3)

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