An Extrapolation from Flight Methodology for a Re-Entry Vehicle Wing Leading Edge Test in a Plasma Wind Tunnel Facility-Reference-Cited by-同舟云学术

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An Extrapolation from Flight Methodology for a Re-Entry Vehicle Wing Leading Edge Test in a Plasma Wind Tunnel Facility

Published:2007-06-15 Issue: Volume: Page:
ISSN:
Container-title:39th AIAA Thermophysics Conference
language:
Short-container-title:

Author:

Di Clemente Marco¹,Rufolo Giuseppe¹,Battista Francesco¹

Affiliation:

1. CIRA

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.2007-3895

Reference15 articles.

1. 1RanuzziG.,S.Borreca,"H3NS:CodeDevelopmentVerificationandValidation",CIRA-CF-06-1017,CIRAInternalReport

2. 2ParkC."AReviewofReactionRatesinHighTemperatureAir",AIAApaper89-1740.

3. 3ParkC.,LeeS.H."ValidationofMulti-TemperatureNozzleFlowCodeNOZNT", AIAAPaper93-2862.

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1. Design and Experimental Study of Spherical Calorimeter in Arc-Heated Wind Tunnel;Lecture Notes in Electrical Engineering;2019

2. Numerical simulation of aerodynamic heating and stresses of chemical vapor deposition ZnS for hypersonic vehicles;Journal of Zhejiang University SCIENCE A;2014-03

3. Hypersonic Test Analysis by Means of Aerothermal Coupling Methodology and Infrared Thermography;AIAA Journal;2013-07

4. European Experimental Reentry Testbed Winglet: From In-Flight Characterization to SCIROCCO Test;AIAA Journal;2012-10

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