Fluid–Thermal Interaction Investigation of Spiked Blunt Bodies at Hypersonic Flight Condition
Author:
Affiliation:
1. Nanjing University of Aeronautics and Astronautics, 210016 Nanjing, People’s Republic of China
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Space and Planetary Science,Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/1.A33370
Reference50 articles.
1. Shock tunnel study of spiked aerodynamic bodies flying at hypersonic Mach numbers
2. MehtaR. C. “Numerical Heat Transfer Study over Spiked Blunt Body at Mach 6.80,” AIAA Paper 2000-0344, 2000.
3. Application of Navier-Stokes flowfield analysis to the aerothermodynamic design of an aerospike-configured missile
4. Hypersonic Drag and Heat-Transfer Reduction Using a Forward-Facing Jet
5. Blunt-Body Wave Drag Reduction Using Focused Energy Deposition
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