Abstract
This study investigates a combined technique of both an active flow control concept that uses counterflowing jets and an aerodisk spike as a new method to significantly modify external flowfields and heat reduction in a hypersonic flow around a nose cone. The coolant gas (Carbon Dioxide and Helium) is chosen to inject from the tip of the nose cone to cool the recirculation region. The gases are considered to be ideal, and the computational domain is axisymmetric. The analysis shows that the counterflowing jet has significant effects on the flowfield and reduces the heat load over the nose cone. The Helium jet is found to have a relatively more effective cooling performance.
This is a preview of subscription content, log in via an institution to check access.
References
Menezes, V., Saravanan, S., Reddy, K.P.J.: Shock tunnel study of spiked aerodynamic bodies flying at hypersonic Mach numbers. Shock Waves 12, 197–204 (2002)
Menezes, V., Kumar, S., Maruta, K., Reddy, K.P.J., Takayama, K.: Hypersonic flow over a multi-step afterbody. Shock Waves 14, 421–424 (2005)
Mohri, K., Hillier, R.: Computational and experimental study of supersonic flow over axisymmetric cavities. Shock Waves 2, 175–191 (2011)
Menezes, V., Saravanan, S., Jagadeesh, G., Reddy, K.P.J.: Experimental investigations of hypersonic flow over highly blunted cones with aero-spikes. AIAA J. 41, 1955–1966 (2003)
Gerdroodbary, M.B., Hosseinalipour, S.M.: Numerical simulation of hypersonic flow over highly blunted cones with spike. Acta Astronaut. 67, 180–193 (2010)
Gerdroodbary, M.B., Bishehsari, S., Hosseinalipour, S.M., Sedighi, K.: Transient analysis of counterflowing jet over highly blunt cone in hypersonic flow. Acta Astronaut. 73, 38–48 (2012)
Gerdroodbary, M.B., Fayazbakhsh, M.A.: Numerical study on heat reduction of various counterflowing jets over highly blunt cone in hypersonic. Int. J. Hypersonics 2(1), 1–13 (2011)
Kulkarni, P.S., Ravi, B.R., Reddy, K.P.J.: Two dimensional Navier-Stokes solutions for transpiration cooling at hypersonic Mach numbers. Shock Waves 13, 497–500 (2004)
Mehta, R.C.: Numerical simulation of supersonic flow past reentry capsules. Shock Waves 15, 31–41 (2006)
Mehta, R.C.: Numerical heat transfer study over spiked blunt bodies at Mach 6.8. J. Spacecr. Rocket 37(5), 700–703 (2000)
Menter, F.R., Kuntz, M., Langtry, R.: Ten years of experience with the SST turbulence model, heat and mass transfer vol. 4, pp. 625–632. Begell House Inc, USA (2003)
Daso, E.O., Pritchett, V.E., Wang, T.S., Ota, D.K., Blankson, I.M., Auslender, A.H.: Dynamic of Shock dispersion and Interaction in supersonic freestreams with counterflowing jets. AIAA J. 47(6), 1313–1326 (2009). doi:10.2514/1.30084
Hayashi, K., Aso, S., Tani, T.: Numerical study of thermal protection by opposing jets. AIAA Paper p. 188 (2005)
Grimaud, J.E., McRee, L.C.: Experimental data on stagnation-point gas injection cooling on hemispherical-cone in a hypersonic arc tunnel. NASA TM X-983 (1964)
Stadler, J.R., Inouye, M.: A method of reducing heat transfer to blunt bodies by air injection. NACA RM A56B27a (1956)
Acknowledgments
The author would like to thank Dr. M. A. Fayazbakhsh for his advice and direction in present work.
Author information
Authors and Affiliations
Corresponding author
Additional information
Communicated by F. Seiler.
Rights and permissions
About this article
Cite this article
Barzegar Gerdroodbary, M. Numerical analysis on cooling performance of counterflowing jet over aerodisked blunt body. Shock Waves 24, 537–543 (2014). https://doi.org/10.1007/s00193-014-0517-4
Received:
Revised:
Accepted:
Published:
Issue Date:
DOI: https://doi.org/10.1007/s00193-014-0517-4