Heat flux and aerodynamics drag reduction of a hypersonic flow with the different tips of the taper spike design parabolic nose cone
Author:
Affiliation:
1. Department of Mechanical Engineering, National Institute of Technology, Jamshedpur, Jharkhand, India
2. Department of Mechanical Engineering, Ramgarh Engineering College, Ramgarh, Jharkhand, India
Publisher
Informa UK Limited
Link
https://www.tandfonline.com/doi/pdf/10.1080/10407782.2024.2302080
Reference41 articles.
1. Shock tunnel study of spiked aerodynamic bodies flying at hypersonic Mach numbers
2. Aerodynamic spike flowfields computed to select optimum configuration at Mach 2.5 with experimental validation
3. Application of Navier-Stokes flowfield analysis to the aerothermodynamic design of an aerospike-configured missile
4. Flowfield Around Spike-Tipped Bodies for High Attack Angles at Mach 4.5
5. Numerical Heat Transfer Study over Spiked Blunt Bodies at Mach 6.8
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1. Reducing aerodynamic drag and heat generation in parabolic nose cones using single and double-disc tapered spikes;Numerical Heat Transfer, Part B: Fundamentals;2024-08-05
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