536
S. Balasubramanian et al.
4 Conclusion
The flow simulations over a ballistic reentry configuration have been done carried out
from low subsonic to hypersonic Mach numbers using Ansys-Fluent with SpalartAllmaras and realizable k-ε turbulence models. Code-to-code comparison has been
carried out using CFD++. The percentage contribution of forebody drag increases
with Mach number, and that of base drag decreases with Mach number. Base drag
is dominant from subsonic to lower supersonic (transonic) and forebody drag is
dominant from higher supersonic to hypersonic Mach number. The total contribution
of viscous drag is very less as compared to pressure drag. The stagnation Cp increases
with an increase in Mach number. Flare part of the configuration contributes to a large
extent in drag generation in transonic and supersonic/hypersonic Mach numbers.
Acknowledgements I express my sincere thanks to Mr. K. Manoharan Sci/Engr’SG’, for reviewing
my paper and giving me the right guidance to correct my mistakes. I would like to specially thanks
to Dr. Dipankar Das Sci/Engr’G’ (Head of the Department), Dr. M. M. Patil Sci/Engr’ H’ (Group
Director), Dr. V. Ashok Sci/Engr’ O.S’ (Deputy Director) who’s given me a constant motivation.
Special thanks to APCF computing facilities, which are allowing me to use the facilities in VSSC.
References
1. Mehta RC (2011) Computations of flowfield over reentry modules at high speed. In: Computational simulations and applications. IntechOpen
2. Mehta RC (2007) Three-dimensional inviscid flowfield computation over various re-entry
configurations. In: Aerospace sciences meeting and exhibit, AIAA paper
3. Balasubramanian S, Vidya G (2019) Base flow characterisation of blunt cone flare configurations at various Mach numbers. Paper got accepted in FMFP conference 2019, PSG College,
Coimbatore
4. Patil MM, Swaminathan S, Kalimuthu R, Mandal JC (2004) Three-dimensional hypersonic flow
computations over reentry capsule using energy relaxation method. J Spacecraft Rockets 41
5. https://web.archive.org/web/20131224103000/http://www.aprsaf.org/data/aprsaf14_data/day1/
SEU10_SRE%20slides%20for%20web.pdf
S. Balasubramanian et al.
4 Conclusion
The flow simulations over a ballistic reentry configuration have been done carried out
from low subsonic to hypersonic Mach numbers using Ansys-Fluent with SpalartAllmaras and realizable k-ε turbulence models. Code-to-code comparison has been
carried out using CFD++. The percentage contribution of forebody drag increases
with Mach number, and that of base drag decreases with Mach number. Base drag
is dominant from subsonic to lower supersonic (transonic) and forebody drag is
dominant from higher supersonic to hypersonic Mach number. The total contribution
of viscous drag is very less as compared to pressure drag. The stagnation Cp increases
with an increase in Mach number. Flare part of the configuration contributes to a large
extent in drag generation in transonic and supersonic/hypersonic Mach numbers.
Acknowledgements I express my sincere thanks to Mr. K. Manoharan Sci/Engr’SG’, for reviewing
my paper and giving me the right guidance to correct my mistakes. I would like to specially thanks
to Dr. Dipankar Das Sci/Engr’G’ (Head of the Department), Dr. M. M. Patil Sci/Engr’ H’ (Group
Director), Dr. V. Ashok Sci/Engr’ O.S’ (Deputy Director) who’s given me a constant motivation.
Special thanks to APCF computing facilities, which are allowing me to use the facilities in VSSC.
References
1. Mehta RC (2011) Computations of flowfield over reentry modules at high speed. In: Computational simulations and applications. IntechOpen
2. Mehta RC (2007) Three-dimensional inviscid flowfield computation over various re-entry
configurations. In: Aerospace sciences meeting and exhibit, AIAA paper
3. Balasubramanian S, Vidya G (2019) Base flow characterisation of blunt cone flare configurations at various Mach numbers. Paper got accepted in FMFP conference 2019, PSG College,
Coimbatore
4. Patil MM, Swaminathan S, Kalimuthu R, Mandal JC (2004) Three-dimensional hypersonic flow
computations over reentry capsule using energy relaxation method. J Spacecraft Rockets 41
5. https://web.archive.org/web/20131224103000/http://www.aprsaf.org/data/aprsaf14_data/day1/
SEU10_SRE%20slides%20for%20web.pdf