Experimental Investigation of Hypervelocity Flow in an Expansion Tunnel-Reference-Cited by-同舟云学术

Experimental Investigation of Hypervelocity Flow in an Expansion Tunnel

Published:2020-06 Issue:6 Volume:58 Page:2776-2783
ISSN:0001-1452
Container-title:AIAA Journal
language:en
Short-container-title:AIAA Journal

Author:

Yuan C. K.¹,Zhou K.²,Hu Z. M.³,Liu Y. F.¹,Jiang Z. L.¹

Affiliation:

1. State Key Laboratory of High Temperature Gas Dynamic, Chinese Academy of Sciences, 100190 Beijing, People’s Republic of China

2. China Academy of Aerospace Aerodynamics, 100074 Beijing, People’s Republic of China

3. State Key Laboratory of High Temperature Gas Dynamic, 100190 Beijing, People’s Republic of China

Funder

National Natural Science Foundation of China

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Reference21 articles.

1. Computational Aerothermodynamic Design Issues for Hypersonic Vehicles

2. Radiating Hypersonic Flow Studies using a Super-Orbital Expansion Tube

3. GrinsteadJ. H.WilderM. C.RedaD. C.CrudenB. A.BogdanoffD. W. “Advanced Spectroscopic and Thermal Imaging Instrumentation for Shock Tube and Ballistic Range Facilities,” NASA Ames Research Center RTO-EN-AVT-186, ARC-E-DAA-TN1396, Moffett Field CA, 2010, https://ntrs.nasa.gov/search.jsp?R=20100027326 [retrieved 13 Jan. 2020].

4. Measurement of Shock Standoff Distance for Sphere in Ballistic Range

5. Shock Detachment Distance on Blunt Bodies in Nonequilibrium Flow

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