Hostname: page-component-78c5997874-v9fdk Total loading time: 0 Render date: 2024-11-13T03:27:02.140Z Has data issue: false hasContentIssue false
  • English
  • Français

Numerical investigation of the effect of disk position on the aerodynamic heating and drag of a spiked blunt body in hypersonic flow

Published online by Cambridge University Press:  18 September 2018

R. Yadav Open the ORCID record for R. Yadav [Opens in a new window] ,
A. Bodavula  and
S. Joshi
R. Yadav*
Affiliation:
Department of Aerospace EngineeringUniversity of Petroleum & Energy StudiesDehradun, India
A. Bodavula
Affiliation:
Department of Aerospace EngineeringUniversity of Petroleum & Energy StudiesDehradun, India
S. Joshi*
Affiliation:
Department of Aerospace EngineeringUniversity of Petroleum & Energy StudiesDehradun, India
*
upes.rajesh@gmail.com
upes.rajesh@gmail.com
Get access Rights & Permissions [Opens in a new window]

Abstract

Detailed numerical simulations have been carried out on a spiked blunt body with multiple hemispherical disks using a commercial CFD code in order to investigate their effectiveness in reducing the aerodynamic drag and heating. The base configuration is a hemispherical cylinder whose diameter is 40 mm with an overall length of 70 mm. The lengths of the aerospikes investigated are 1, 1.5, 2 and 2.5 times the base diameter of the cylinder and the radii of the aerodisks are varied between 0.05, 0.1, 0.15 and 0.2 times the diameter of the cylinder. Besides these, the position of the aerodisks is varied with the rearmost aerodisk placed at 25%, 50% and 75% along the length of the aerospike and the intermediate aerodisk for three-disk cases, positioned at 25%, 50% and 75% of the distance between the front and the rearmost disk. All the investigations have carried out at a freestream Mach number of 6.2 and Reynolds number of 2.64 × 107/m. It has been observed that the multidisk spikes are advantageous for the purpose of reduction of both aerodynamic drag and heating at hypersonic speed. The two aerodisk spiked configurations show better results in terms of aerodynamic heating and drag in comparison to the single-disk aerospikes while the three-disk spikes yield only a marginal reduction in aerodynamic drag over the two-disk configurations. For reduction of heat fluxes and heat transfer rates though, the three-disk configurations are extremely advantageous and give much larger reductions are compared to the two-disk configurations.

Keywords

AerospikeAerodynamic heatingDrag reductionHypersonic flows
Type
Research Article
Information
The Aeronautical Journal , Volume 122 , Issue 1258 , December 2018 , pp. 1916 - 1942
Copyright
© Royal Aeronautical Society 2018 

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

REFERENCES

1. Anderson, J.D.. Hypersonic and High Temperature Gas Dynamics, AIAA, 2006, Virginia, US.Google Scholar
2. Wang, Z., Sun, X., Huang, W., Li, S. and Yan, L. Experimental investigation on drag and heat flux reduction in supersonic/hypersonic flows: a survey, Acta Astronautica, 2016, 129, pp 95–110.Google Scholar
3. Alexander, S.R. Results of Tests to Determine the Effect of a Conical Windshield on the Drag of a Bluff Body at Supersonic Speeds, NACA RM L6K08a, January 1947.Google Scholar
4. Bogdonoff, S.M. and Vas, I.E. Preliminary investigations of spiked bodies at hypersonic speeds, J Aerospace Sciences, 1959, 26, (2), pp 65–74.Google Scholar
5. Crawford, D.H. Investigation of the Flow Over a Spiked-Nose Hemisphere-Cylinder, NASA TN-D-118, December 1959.Google Scholar
6. Maull, D.J. Hypersonic flow over axially symmetric spiked bodies, J Fluid Mechanics, 1960, 8, (P.4), pp 584–92.Google Scholar
7. Wood, C.J. Hypersonic flow over spiked cones, J Fluid Mechanics, 1961, 12, (Pt. 4), pp 614–24.Google Scholar
8. Holden, M. Experimental studies of separated flows at hypersonic speeds. Part I—separated flows over axisymmetric spiked bodies, AIAA J, 1966, 4, (4), pp 591–599.Google Scholar
9. McGhee, R.J. and Staylor, W.F. Aerodynamic Investigation of Sharp Cone-Cylinder Spikes on 1200 Blunted Cones at Mach Numbers of 3, 4.5, and 6, NASA TN D-5201, 1969.Google Scholar
10. Staylor, W.F. Flow-Field Investigation for Large-Angle Cones with Short Spikes at a Mach Number of 9.6, NASA TN D-5754, 1970.Google Scholar
11. Yamauchi, M., Fujii, K. and Higashino, F. Numerical investigation of supersonic flows around a spiked blunt body, J Spacecraft and Rockets, 1995, 32, (1), pp 32–42.Google Scholar
12. Kalimuthu, R., Mehta, R.C. and Rathakrishnan, E. Drag reduction for spike attached to blunt-nosed body at Mach 6, J Spacecraft and Rockets, 2010, 47, (1), pp 219–22.Google Scholar
13. Stadler, J.R. and Neilson, H.V. Heat Transfer from a Hemisphere Cylinder Equipped with Flow Separation Spikes, NACA TN-3287, 1954.Google Scholar
14. Kalimuthu, R., Mehta, R.C. and Rathakrishnan, E. Experimental investigation on spiked body in hypersonic flow, Aeronautical J, 2008, 112, (1136), pp 593–8.Google Scholar
15. Jones, J.J. Experimental Drag Coefficients of Round Noses with Conical Wind-Shields at Mach Number 2.72, NACA RM L55E10, June 1955.Google Scholar
16. Beastall, D. and Turner, J. The Effect of a Spike Protruding in Front of a Bluff: Body at Supersonic Speeds, Aeronautical Research Council, R. & M. No. 3007, 1957.Google Scholar
17. Menezes, V., Saravanan, S. and Reddy, K.P.J. Shock tunnel study of spiked aerodynamic bodies flying at hypersonic Mach numbers, Shock Waves, 2002, 12, (1), pp 197–204.Google Scholar
18. Gopalan, J., Menezes, V., Reddy, K.P.J., Hashimoto, T., Sun, M., Saito, T. and Takayama, K. Flowfields of a large-angle, spiked blunt cone at hypersonic Mach numbers, Transactions of Japan Soc Aero Space Science, 2005, 48, (160), pp 110–116.Google Scholar
19. Heubner, L.D., Mitchell, A.M. and Boudreaux, E.J. Experimental Results on the Feasibility of an Aerospike for Hypersonic Missiles, AIAA paper, 95-0737, January 1995.Google Scholar
20. Gauer, M. and Paull, A. Numerical investigation of a spiked blunt nose cone at hypersonic speeds, J Spacecrafts and Rockets, 2008, 45, (3), pp 459–471.Google Scholar
21. Gerdroodbary, M.B. and Hosseinalipour, S.M. Numerical simulation of hypersonic flow over highly blunted cones with spike, Acta Astronautica, 2010, 67, pp 180–193.Google Scholar
22. Zhang, R., Huang, W., Yan, L., Li, L., Li, S. and Moradi, R. Numerical investigation of drag and heat flux reduction mechanism of the pulsed counterflowing jet on a blunt body in supersonic flows, Acta Astronautica, 2018, 146, pp 123–133.Google Scholar
23. Huang, W., Zhang, R., Yan, L., Ou, M. and Moradi, R. Numerical experiment on the flow field properties of a blunted body with a counterflowing jet in supersonic flows, Acta Astronautica, 2018, 147, pp 231–240.Google Scholar
24. Deng, F., Xie, F., Qin, N., Huang, W., Wang, L. and Chu, H. Drag reduction investigation for hypersonic lifting-body vehicles with aerospike and long penetration mode counterflowing jet, Aerospace Science and Technology, 2018, 76, pp 361–373.Google Scholar
25. Huang, W., Jiang, Y., Yan, L. and Liu, J. Heat flux reduction mechanism induced by a combinational opposing jet and cavity concept in supersonic flows, Acta Astronautica, 2016, 121, pp 164–171.Google Scholar
26. Sun, X., Guo, Z., Huang, W., Li, S. and Yan, L. Drag and heat reduction mechanism induced by a combinational novel cavity and counterflowing jet concept in hypersonic flows, Acta Astronautica, 2016, 126, pp 109–119.Google Scholar
27. Sun, X., Guo, Z., Huang, W., Li, S. and Yan, L. A study of performance parameters on drag and heat flux reduction efficiency of combinational novel cavity and opposing jet concept in hypersonic flows, Acta Astronautica, 2017, 131, pp 204–225.Google Scholar
28. Eghlima, Z. and Mansour, M. Drag reduction for the combination of spike and counterflow jet on blunt body at high Mach number flow, Acta Astronautica, 2017, 133, pp 103–110.Google Scholar
29. Gerdroodbary, M.B., Imani, M. and Ganji, D.D. Heat reduction using counterflowing jet for a nose cone with aerodisk in hypersonic flow, Aerospace Science and Technology, 2014, 39, pp 652–665.Google Scholar
30. Huang, W., Liu, J. and Xia, Z. Drag reduction mechanism induced by a combinational opposing jet and spike concept in supersonic flows, Acta Astronautica, 2015, 115, pp 24–31.Google Scholar
31. Eghlima, Z., Mansour, K. and Fardipour, K. Heat transfer reduction using combination of spike and counterflow jet on blunt body at high Mach number flow, Acta Astronautica, 2018, 143, pp 92–104.Google Scholar
32. Huang, W. A survey of drag and heat reduction in supersonic flows by a counterflowing jet and its combinations, J Zhejiang University – Science A (Applied Physics & Engineering), 2015, 16, (7), pp 309, 551–561.Google Scholar
33. Yadav, R. and Guven, U. Aerothermodynamics of a hypersonic projectile with a double-disk aerospike, Aeronautical J, 2013, 117, (1195), pp 913–928.Google Scholar
34. Yadav, R., Velidi, G. and Guven, U. Aerothermodynamics of generic re-entry vehicle with a series of aerospikes at nose, Acta Astronautica, 2014, 96, pp 1–10.Google Scholar
35. 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 33–44.Google Scholar
36. Maru, Y., Kobayashi, H., Takeuchi, S. and Sato, T. Flow oscillation characteristics in conical cavity with multiple disks, J Spacecraft and Rockets, 2007, 44, (5), pp 1012–1020.Google Scholar
37. Liou, M.S A sequel to AUSM: AUSM+, J Computational Physics, 1996, 129, pp 364–382.Google Scholar
38. Roy, C.J. and Blottner, F.G. Review and assessment of turbulence models for hypersonic flows, Progress in Aerospace Sciences, 2006, 42, pp 469–530.Google Scholar
39. Roy, C.J. and Blottner, F.G. Assessment of One- and Two-Equation Turbulence Models for Hypersonic Transitional Flows, AIAA paper 2000-132, 38th AIAA Aerospace Sciences Meeting, Reno, NV, 10–13 January 2000.Google Scholar
40. Paciorri, R., Dieudonn, W., Degrez, G., Charbonnier, J.M. and Deconink, H. Exploring the validity of the Spalart–Allmaras turbulence model for hypersonic flows, J Spacecraft and Rockets, 1998, 35, (2), 121–126.Google Scholar
41. Spalart, P. and Allmaras, S. A one-equation turbulence model for aerodynamic flows, La Recherché Aerospatiale, 1994, 1, pp 5–21.Google Scholar
42. Dacles-Mariani, J., Zilliac, G.G., Chow, J.S. and Bradshaw, P. Numerical/experimental study of a wingtip vortex in the near field. AIAA J, 1995, 33, (9), pp 1561–1568.Google Scholar
43. Huang, W., Li, L., Yan, L. and Zhang, T. Drag and heat flux reduction mechanism of blunted cone with aerodisks, Acta Astronautica, 2017, 138, pp 168–175.Google Scholar
44. Roy, C.J. and Blottner, F.G. Further Assessment of One- and Two-Equation Turbulence Models for Hypersonic Transitional Flows, AIAA Paper 2001-0210.Google Scholar
45. Huang, W., Yan, L., Liu, J., Jin, L. and Tan, J. Drag and heat reduction mechanism in the combinational opposing jet and acoustic cavity concept for hypersonic vehicles, Aerospace Science and Technology, 2015, 42, pp 407–414.Google Scholar