A Study on the Reduction of Drag and Heat Transfer on a Conventional Hypersonic Nose Cone

Document Type : Full Length Research Article

Authors

1 Qadr Aerodynamic Institute, Imam Hossein University, Tehran, 1698715461, Iran

2 Department Aerospace Engineering, Faculty of New Sciences and Technologies, Semnan University, Semnan, 19111-35131, Iran

Abstract

In the present study, the effect of jet injection on two geometries—single-cone and double-cone—subjected to hypersonic flow is investigated. The simulations are performed using ANSYS-Fluent software. The baseline case is one where the nose lacks injection. The single-cone nose is tested at Mach 6, and the double-cone nose at Mach 5.4. The results show that increasing injection pressure results in a drag coefficient reduction of 49.2% for the single-cone geometry and 62.7% for the double-cone geometry, compared to the baseline. Additionally, the heat flux decreases by 60% for the single-cone nose and 41.3% for the double-cone nose. Higher injection pressure leads to an increase in bow shock standoff distance upstream of both the single-cone and double-cone noses. Increasing injection temperature has minimal impact on the drag coefficient and pressure distribution on the surface of the single-cone nose but significantly reduces the Stanton number, thereby decreasing heat transfer and enhancing nose cooling. Increasing the injection diameter from zero to 5 mm in the single-cone nose results in a 23% reduction in drag coefficient, while for the double-cone geometry, increasing the diameter to 16.5 mm reduces the drag coefficient by 75.04%. Changing the fluid type from air to a gas mixture decreases the maximum Stanton number by 19.3%.

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References

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Journal of Heat and Mass Transfer Research
Volume 12, Issue 2 - Serial Number 24
In Progress
November 2025
Pages 393-411

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History

  • Receive Date: 31 December 2024
  • Revise Date: 06 February 2025
  • Accept Date: 16 March 2025

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