Mathematics and Computational Sciences

Computational investigation of drag reduction on a large blunt Cone-Flare body in hypersonic turbulent flow using a Counter-Flow jet at various angle of attack

Articles in Press

Document Type : Original Article

Authors

S Aruna 1
M Kayalvizhi 2
S.V Anandhi 3
B Amutha 1
N Indumathi 4

1 Department of Mathematics, St.Joseph’s College of Engineering, OMR, Chennai, 600 119, Tamilnadu, India.

2 Department of Mathematics, Government Polytechnic, Daman, India.

3 Department of Artificial Intelligence and Data Science, Ramco Institute of Technology, Rajapalayam, India.

4 Department of Mathematics, Sri Ramakrishna Engineering College, Coimbatore, India.

https://doi.org/10.30511/mcs.2026.2077646.1626
Abstract
The large blunt-nosed body is a common shape used in the design of hypersonic vehicles. The angle of attack (α) in these vehicles introduces several challenges that can significantly affect performance. The primary issues caused by α in hypersonic vehicles include increased drag, thermal loads, flow separation, structural stress, control and stability difficulties, and complex shock wave interactions. Controlling α is critical for optimizing performance and preventing damage or failure during re-entry or high-speed manoeuvres. The current effort intends to minimise drag for a large blunt cone-flare body in hypersonic turbulent flow by maximising the angle of attack with a counter-flow jet. The massive blunt cone-flare body was simulated and the hypersonic flow conditions were set. The axisymmetric Navier-Stokes equations were numerically analysed using the shear stress transport model. Total drag, skin friction drag, and pressure drag were measured with and without the jet. Contours of Mach number and temperature were analyzed to describe the flow pattern. Optimal jet conditions for drag mitigation were identified.

Keywords

Drag
Jet
Large Blunt Cone Flare Body
Angle of Attack
Subjects

[1] Aruna, S., & Anjali Devi, S. P. (2012). Procedia Engineering, 38, 3635–3643. 
[2] Chinnappan, A. K., Malaikannan, G., & Kumar, R. (2017). Aerospace Science and Technology, 66, 119–129. 
[3] Deng, F., Xie, F., & Qin, N. (2018). Aerospace Science and Technology, 76, 361–372. 
[4] Gao, W., Wei, M., & Huang, S. (2023). Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering, 238(9), 1–15. 
[5] Gerdroodbary, M. B., & Hosseinalipour, S. M. (2010). Acta Astronautica, 67, 180–193. 
[6] Li, S.-B., Wang, Z.-G., Barakos, G. N., Huang, W., & Steijl, R. (2016). Acta Astronautica, 127, 120–134. 
[7] Luo, S., Li, D., Wang, J., Dai, Y., & Feng, Y. (2025). Drag reduction and thermal protection efficiencies of combinational spike and opposing jet with different forebody geometries in hypersonic flows. Applied Thermal Engineering, 278, Article 125000.
[8] Savino, R., & Paterna, D. (2005). Computers & Fluids, 34, 859–878.
[9] Schrijer, F. F. J. (2003). Transient heat transfer measurements in a short duration hypersonic facility on a blunted cone-flare using QIRT (Doctoral dissertation, Delft University of Technology).

Mathematics and Computational Sciences

Articles in Press, Accepted Manuscript
Available Online from 29 May 2026

  • Receive Date 14 November 2025
  • Revise Date 29 May 2026
  • Accept Date 29 May 2026

Home

Submit Manuscript

Reviewers

Contact Us