Experimental and numerical investigation of smooth turbine-based combined-cycle inlet mode transition-Reference-Cited by-同舟云学术

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Experimental and numerical investigation of smooth turbine-based combined-cycle inlet mode transition

Published:2017-01 Issue: Volume:60 Page:124-130
ISSN:1270-9638
Container-title:Aerospace Science and Technology
language:en
Short-container-title:Aerospace Science and Technology

Author:

Liu Jun,Yuan Huacheng,Hua Zhengxu,Chen Wenfang,Ge Ning

Funder

Funding for Outstanding Doctoral Dissertation in NUAA

Funding of Jiangsu Innovation Program for Graduate Education

Fundamental Research Funds for the Central Universities

Publisher

Elsevier BV

Subject

Aerospace Engineering

Reference20 articles.

1. The Hyper-X Flight Systems Validation Program;Redifer,2007

2. Achievements Obtained for Sustained Hypersonic Flight within the LAPCAT Project;Steelant,2008

3. Hyper-X: foundation for future hypersonic launch vehicles;McClinton;Acta Astronaut.,2005

4. The Benefits of Hypersonic Airbreathing Launch Systems for Access to Space;Bilardo,2003

5. TSTO Reusable Launch Vehicles Using Airbreathing Propulsion;Hank,2006

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2. Flow Coefficient and Starting Performance Prediction of Variable Geometry Curved Axisymmetric Inlet;Aerospace;2023-05-27

3. Characteristics of Combined-Cycle Inlet During Mode Transition in Off-Design State;AIAA Journal;2023-05

4. Distributed Fluidic Control Method for Alleviating Rapid Movement of Shock Train;AIAA Journal;2022-11

5. Performance evaluation for a combined power generation system of closed-Brayton-cycle and thermoelectric generator with finite cold source at room temperature on hypersonic vehicles;Energy;2022-09

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