Abstract
An experimental campaign was carried out to investigate the feasibility of using mass transfer cooling techniques such as thermal protection system (TPS) for Martian entry spacecraft’s configurations. The tests were performed using hypersonic shock tunnels HST2 and HST3, at Laboratory for Hypersonic and Shock Wave Research (LHSR), IISc, Bangalore, simulating low (1.5 km/s) and high enthalpy (2.5 km/s) flow conditions, respectively. A large angle (60° apex angle) blunt sphere-cone configuration was used as test model, and heat transfer rate to the model surface was measured using platinum thin film sensors. Film and transpiration cooling were the two techniques investigated using nitrogen and helium gas as coolants. The investigations showed that these techniques resulted in reduction in heat transfer, and it was more effective for the high enthalpy test case.
Keywords
Reprinted by permission of the American Institute of Aeronautics and Astronautics, Inc, from Experimental Investigation of Heat Flux Mitigation During Martian Entry by Coolant Injection, Journal of Spacecraft and Rockets, Vol. 51, No. 4(2014), pp. 1363–1368 & Experimental Investigation on Transpiration Cooling Effectiveness for Spacecraft Entering Martian Atmosphere, AIAA Journal Vol. 54, No. 9(2016), pp. 2922–2926. Copyright © AIAA.
Access this chapter
Tax calculation will be finalised at checkout
Purchases are for personal use only
References
Anderson JD (1990) Modern compressible flow. MacGraw Hill Book Company, ISBN 0-07-124136-1
Anderson JD (1989) Hypersonics and high temperature gas dynamics. McGraw Hill Publications
Sheikh UA (2014) Re-entry radiation aerothermodynamics in the vacuum ultraviolet. Ph.D. Dissertation, University of Queensland
Peter FI, Donn BK (1987) High-speed aerodynamics of several blunt cone configurations. J Spacecraft Rockets 24(127)
Stewart DA, Chen YK (1994) Hypersonic convective heat transfer over 140 blunt cones in different gases. J Spacecraft Rockets 31(735)
Hollis BR, John NP (1997) High enthalpy aero thermodynamics of a mars entry vehicle part 1: experimental results. J Spacecraft Rocket 34(449)
en.wikipedis.org/wiki/Atmospheric_entry#Thermal_protection_ systems
Finley PJ (1966) The flow of a jet from a body opposing a supersonic free stream. J Fluid Mech 26(2):337–368
Sahoo N, Kulkarni V, Saravanan S, Jagadeesh G, Reddy KPJ (2005) Film cooling effectiveness on a large angle blunt cone flying at hypersonic speed. Phys Fluids 17:036102
Kulkarni V, Jagadeesh G, Reddy KPJ (2008) Enhancement in counterflow drag reduction by supersonic jet in high enthalpy flows. Phys Fluids 20:016103
Warren CHE (1959) An experimental investigation of the Effect of ejecting a coolant gas at the nose of a bluff body. J Fluid Mech 8(3):400–416
Libby PA, Cresci RJ (1961) Experimental investigation of downstream influence of stagnation point mass transfer. J Aerosp Sci 26(6):51–63
Baron JR, Alzner E (1962) An experimental investigation of a two-layer invicid shock cap due to blunt-body nose injection. J Fluid Mech 15(3):442–448
Romeo DJ, Sterrett JR (1963) Exploratory investigation of the effect of a forward-facing jet on the bow shock of a blunt body in a mach number 6 free stream. NASA TN D-1605
Edward R, Barber Jr (1965) An experimental investigation of stagnation point injection. J Spacecraft Rockets 2(5):770–774
Sriram R, Jagadeesh G (2009) Film cooling at hypersonic mach numbers using forward facing array of micro-jets. Int J Heat Mass Transf 54:3654–3664
Cook WJ, Felderman EJ (1966) Reduction of data from thin-film heat transfer gages: a concise numerical technique. AIAA J 4–3:561–562
CHEMKIN (2012) Chemical Kinetic Software, Ver. 10113. http://www.reationdesign.com/lobby/open/index.html
Greuel D, Herbertz A, Haidn OJ, Ortelt M, Hald H (2004) Transpiration cooling applied to C/C liners of cryogenic liquid rocket engines. AIAA Paper 2004–3682
Leo TC, Howard SC (1955) Exploratory test of transpiration cooling on a porous 8 cone at M = 2.05 using nitrogen gas, helium gas and water as the coolants. NACA RM L55C29
Bernard R (1957) Exploratory investigation of transpiration cooling of a 40 double wedge using nitrogen and helium as coolants at stagnation temperatures of 1295 to 2910 F. NACA RM L57F11
Hirotaka O, Fujita K, Ito T (2007) Application of the transpiration cooling method for reentry vehicles. AIAA Paper 2007-12029
Yuan QL, Pei XJ, Shao SJ, JI GS (2010) Transpiration cooling of a nose cone by various foreign gases. Int J Heat Mass Transfer 53:5364–5372
Sreekanth M, Reddy NM (1994) Transpiration cooling analysis at hypersonic mach numbers using Navier-Stokes equations. AIAA Paper 94-2075
Sreekanth M, Reddy NM (1995) Numerical simulation of transpiration cooling over blunt bodies at hypersonic mach number. AIAA Paper 95-2082
Kulkarni VN (2003) Numerical and experimental investigation of transpiration cooling in carbon dioxide atmosphere at hypersonic mach numbers. M.Sc. Dissertation, Department of Aerospace Engineering, Indian Institute of Science, Bangalore
Acknowledgements
We would like to thank Defence Research and Development Organization (DRDO) for the financial support provided for carrying out these investigations. We also thank American Institute of Aeronautics and Astronautics, Inc. for providing us the copyright permission.
Author information
Authors and Affiliations
Corresponding author
Editor information
Editors and Affiliations
Rights and permissions
Copyright information
© 2020 Springer Nature Singapore Pte Ltd.
About this chapter
Cite this chapter
Mohammed Ibrahim, S., Reddy, K.P.J. (2020). An Experimental Investigation of Mass Transfer Cooling Techniques for Atmospheric Entry Vehicles. In: Gupta, A., De, A., Aggarwal, S., Kushari, A., Runchal, A. (eds) Innovations in Sustainable Energy and Cleaner Environment. Green Energy and Technology. Springer, Singapore. https://doi.org/10.1007/978-981-13-9012-8_3
Download citation
DOI: https://doi.org/10.1007/978-981-13-9012-8_3
Published:
Publisher Name: Springer, Singapore
Print ISBN: 978-981-13-9011-1
Online ISBN: 978-981-13-9012-8
eBook Packages: EnergyEnergy (R0)