Investigation of Design Method for the Inward Turning Inlet with Controlled Intake Curve-Reference-Cited by-同舟云学术

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Investigation of Design Method for the Inward Turning Inlet with Controlled Intake Curve

Published:2017-03-02 Issue: Volume: Page:
ISSN:
Container-title:21st AIAA International Space Planes and Hypersonics Technologies Conference
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Author:

Li Yongzhou¹,Zhang Kun Yuan²,Sun Di³

Affiliation:

1. China Aerospace System Development Research Center

2. Nanjing University of Aeronautics and Astronautics

3. Xi’an Institute of Aerospace Propulsion Technology

Publisher

American Institute of Aeronautics and Astronautics

Link

https://arc.aiaa.org/doi/pdf/10.2514/6.2017-2423

Reference20 articles.

1. 1BilligF.S.,andJacobsenL.S."Comparisonofplanarandaxisymmetricflowpathsforhydrogenfueledspaceaccessvehicle," AIAA2003-4407,2003.

2. 2YouY. C. "An overviewoftheadvantagesand concernsofhypersonicinward turninginlets,"AIAA2011-2269,2011.

3. 4Bulman M. J., and SiebenhaarA. "Therebirthofroundhypersonicpropulsion,"AIAA2006-5035,2006.

4. 5Zhang K. Y. "Research progress of hypersonic inlet inverse design based on curved shock compression system," AIAA2015-3647,2015.

Cited by 1 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. Design studies on NAGIC flowfield with application to integrated irregular-shaped supersonic inlet;Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering;2022-08-29

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