Aeroelastic Study of the Splitter Plate in Turbine-Based Combined-Cycle Inlet-Reference-Cited by-同舟云学术

Aeroelastic Study of the Splitter Plate in Turbine-Based Combined-Cycle Inlet

Published:2018-09 Issue:5 Volume:55 Page:1914-1928
ISSN:0021-8669
Container-title:Journal of Aircraft
language:en
Short-container-title:Journal of Aircraft

Author:

Qin Qihao¹,Xu Jinglei¹,Guo Shuai¹

Affiliation:

1. Nanjing University of Aeronautics and Astronautics, 210016 Nanjing, People’s Republic of China

Funder

Natural Science Fund of China

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Link

https://arc.aiaa.org/doi/pdf/10.2514/1.C034649

Reference39 articles.

1. Critical Issues in TBCC Modeling

2. Axisymmetric Inlet Design for Combined-Cycle Engines

3. SandersB. W.WeirL. J. “Aerodynamic Design of a Dual-Flow Mach 7 Hypersonic Inlet System for a Turbine-Based Combined-Cycle Hypersonic Propulsion System,” NASA CR-2008-215214, 2008.

4. Highlights from a Mach 4 Experimental Demonstration of Inlet Mode Transition for Turbine-Based Combined Cycle Hypersonic Propulsion

5. SaundersJ. D.StueberT. J.ThomasS. R.SuderK. L.WeirL. J.SandersB. W. “Testing of the NASA Hypersonics Project’s Combined Cycle Engine Large Scale Inlet Mode Transition Experiment (CCE LIMX),” NASA TM-2012-217217, Jan. 2012.

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