On the Current Limits of Simulating Gas Giant Entry Flows in an Expansion Tube-Reference-Cited by-同舟云学术

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On the Current Limits of Simulating Gas Giant Entry Flows in an Expansion Tube

Published:2015-07-02 Issue: Volume: Page:
ISSN:
Container-title:20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
language:
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Author:

James Christopher M.,Gildfind David,Morgan Richard G.,Lewis Steven W.,Fahy Elise J.

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.2015-3501

Reference38 articles.

1. Galileo Probe Heat Shield Ablation Experiment

2. Spallation of the Galileo probe heat shield

3. Ablation of Galileo Probe heat-shield models in a ballistic range

4. Calculation of radiation from argon shock layers

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1. Experimentally Simulating Giant Planet Entry in an Expansion Tube;Journal of Spacecraft and Rockets;2020-07

2. Capabilities and limitations of existing hypersonic facilities;Progress in Aerospace Sciences;2020-02

3. Performance Optimization of X3R: A New Reflected Shock Tunnel Mode for the X3 Expansion Tube;2018 Aerodynamic Measurement Technology and Ground Testing Conference;2018-06-24

4. Venus Entry Flow over a Decomposing Aeroshell in X2 Expansion Tube;Journal of Thermophysics and Heat Transfer;2018-04

5. Experimentally Simulating Gas Giant Entry in an Expansion Tube;21st AIAA International Space Planes and Hypersonics Technologies Conference;2017-03-02

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