Flow Path and Interaction Analysis in a Hydrogen Transpiration Cooled Scramjet Model Combustor-Reference-Cited by-同舟云学术

Flow Path and Interaction Analysis in a Hydrogen Transpiration Cooled Scramjet Model Combustor

Published:2019-08-16 Issue: Volume: Page:
ISSN:
Container-title:AIAA Propulsion and Energy 2019 Forum
language:
Short-container-title:

Author:

Strauss Friedolin T.¹,General Stephan¹,Manfletti Chiara²,Schlechtriem Stefan¹

Affiliation:

1. German Aerospace Center (DLR)

2. ESA

Publisher

American Institute of Aeronautics and Astronautics

Reference40 articles.

1. Preliminary Design of an Aerodynamic Protection for the scramjet Engine Inlet of the Brazilian Technological Demonstrator scramjet 14-X S

2. Langener, T. "A Contribution to Transpiration Cooling for Aerospace Applications Using CMC Walls," PhD thesis,University of Stuttgart, Germany, 2011.

3. Greuel, D. "Investigations on Momentum and Mass Transport in Effusion Cooled Rocket Combustion Chambers Made of Fibre Ceramics," PhD thesis,RWTH Aachen, Germany, 2013.

Cited by 3 articles. 订阅此论文施引文献订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. Lateral Wall Temperature Effects in a Transpiration Cooled Scramjet Model Combustor with Shock-Boundary Layer Interaction;AIAA Propulsion and Energy 2021 Forum;2021-07-28

2. Lateral Wall Pressure Effects in a Transpiration Cooled Scramjet Model Combustor with Shock-Boundary Layer Interaction;AIAA Propulsion and Energy 2020 Forum;2020-08-17

3. Wall Pressure Effects and Shock-Boundary Layer Interactions in a Transpiration Cooled Scramjet Model Combustor;23rd AIAA International Space Planes and Hypersonic Systems and Technologies Conference;2020-03-10