Effect of the axial cavity with an opposing high-pressure jet combination in a Mach 6 flow condition-Reference-Cited by-同舟云学术

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Effect of the axial cavity with an opposing high-pressure jet combination in a Mach 6 flow condition

Published:2021-01 Issue: Volume:178 Page:335-348
ISSN:0094-5765
Container-title:Acta Astronautica
language:en
Short-container-title:Acta Astronautica

Author:

Sudarshan B.^ORCID,Rao Srisha M.V.^ORCID,Jagadeesh G.,Saravanan S.

Publisher

Elsevier BV

Subject

Aerospace Engineering

Reference79 articles.

1. Investigation on thermal performance of high temperature multilayer insulations for hypersonic vehicles under aerodynamic heating condition;Ji;Appl. Therm. Eng.,2014

2. Numerical investigation on a double layer combined cooling structure for aerodynamic heat control of hypersonic vehicle leading edge;Ding;Appl. Therm. Eng.,2020

3. Modeling of aerodynamic heat flux and thermoelastic behavior of nose caps of hypersonic vehicles;Persova;Acta Astronaut.,2017

4. Optimum design of ablative thermal protection systems for atmospheric entry vehicles;Riccio;Appl. Therm. Eng.,2017

5. The design of thermal management system for hypersonic launch vehicles based on active cooling networks;Gou;Appl. Therm. Eng.,2019

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1. Aerothermal and aerodynamic characteristics of reusable hypersonic vehicles with heat transfer minimised sweepback;The Aeronautical Journal;2024-04-11

2. Heat and drag reduction on the hypersonic nose with a nexus between active and passive control methods;Physics of Fluids;2024-01-01

3. Investigation of drag reduction mechanism for blunt bodies with plasma spikes;Physics of Fluids;2023-08-01

4. Investigation on the opposing jet penetration mode transition mechanism in the hypersonic flow;The Aeronautical Journal;2023-06-21

5. Numerical investigation on the characteristics of cavity-transpiration combined cooling for hypersonic vehicle leading edge;Applied Thermal Engineering;2023-05

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