Aerodynamic Drag Reduction Using Aerospikes for Large Angle Blunt Cone Flying at Hypersonic Mach Number-Reference-Cited by-同舟云学术

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Aerodynamic Drag Reduction Using Aerospikes for Large Angle Blunt Cone Flying at Hypersonic Mach Number

Published:2002-06-24 Issue: Volume: Page:
ISSN:
Container-title:22nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference
language:
Short-container-title:

Author:

Menezes Viren¹,Saravanan S.¹,Jagadeesh G.¹,Reddy K. P. J¹

Affiliation:

1. Indian Institute of Science

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.2002-2709

Reference10 articles.

1. Experimental results on the feasibility of an aerospike for hypersonic missiles. AIAA Paper 95-0737 (1995)

2. Flow field around spike-tipped bodies. AIAA Paper 2001-2464 (2001)

3. ELECTRICAL DISCHARGE TECHNIQUE FOR THREE-DIMENSIONAL FLOW FIELD VISUALIZATION IN HYPERSONIC SHOCK TUNNEL

Cited by 4 articles. 订阅此论文施引文献订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. Drag Reduction of a Hemispherical Body Adopting Spike at Supersonic Speed;Journal of Aerospace Sciences and Technologies;2023-08-15

2. Effects of Heat Addition on Wave Drag Reduction of a Spiked Blunt Body;International Journal of Aerospace Engineering;2021-01-16

3. Shock Tunnels and Hypersonic Research in IISc, Bangalore;Experimental Methods of Shock Wave Research;2015-11-01

4. Hypersonic wave drag reduction in re-entry capsules using concentrated energy deposition;Shock Waves;2005

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