Development of a Mach 5 Nonequilibrium-Flow Wind Tunnel-Reference-Cited by-同舟云学术

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Development of a Mach 5 Nonequilibrium-Flow Wind Tunnel

Published:2012-10 Issue:10 Volume:50 Page:2255-2267
ISSN:0001-1452
Container-title:AIAA Journal
language:en
Short-container-title:AIAA Journal

Author:

Nishihara M.,Takashima K.,Jiang N.,Lempert W. R.,Adamovich I. V.,Rich J. W.,Doraiswamy S.,Candler G. V.

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Link

http://arc.aiaa.org/doi/pdf/10.2514/1.J051605

Reference31 articles.

1. Transition Delay in Hypervelocity Boundary Layers by Means of CO2/Acoustic Instability Interactions

2. Carbon Dioxide Injection for Hypervelocity Boundary Layer Stability

3. Oxygen Atoms' Effect on Vibrational Relaxation of Nitrogen in Blunt-Body Flows

4. Mach 5 bow shock control by a nanosecond pulse surface dielectric barrier discharge

5. Electrically Excited, Supersonic Flow Carbon Monoxide Laser

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1. Characterization of a Glow Discharge in a Tripped Hypersonic Boundary Layer;J THERMOPHYS HEAT TR;2024

2. Thermomechanical Relaxation of Vibrationally Excited NO in a Hypersonic Turbulent Boundary Layer;AIAA SCITECH 2024 Forum;2024-01-04

3. Nitric Oxide Planar Laser Induced Fluorescence Rotational Thermometry Characterization of a Hypersonic Boundary Layer;AIAA SCITECH 2024 Forum;2024-01-04

4. The Characterization of a DC Glow Discharge in a Tripped Hypersonic Boundary Layer;AIAA SCITECH 2024 Forum;2024-01-04

5. Electric field distribution in a non-self-sustained RF discharge with ionization generated by Ns discharge pulses;Plasma Sources Science and Technology;2022-12-01

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