Inverse design method on scramjet nozzles based on maximum thrust theory-Reference-Cited by-同舟云学术

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Inverse design method on scramjet nozzles based on maximum thrust theory

Published:2020-01 Issue: Volume:166 Page:162-171
ISSN:0094-5765
Container-title:Acta Astronautica
language:en
Short-container-title:Acta Astronautica

Author:

Yu Kaikai,Chen Yile^ORCID,Huang Shuai^ORCID,Xu Jinglei^ORCID

Funder

National Natural Science Foundation of China

Fundamental Research Funds for the Central Universities

Publisher

Elsevier BV

Subject

Aerospace Engineering

Reference25 articles.

1. Scramjet Propulsion;Curran,2001

2. A review of design issues specific to hypersonic flight vehicles;Sziroczak;Prog. Aerosp. Sci.,2016

3. History of scramjet propulsion development;Seleznev;J. Phys. Conf. Ser.,2018

4. NASA's Hypersonic Research Engine Project: A Review, TM 107759;Andrews,1994

5. Propulsion aspects of hypersonic turbo-ramjet-engines with special emphasis on nozzle/aftbody integration;Herrmann,1991

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1. Flow Effects and Propulsion Performance on Various Single Expansion Ramp Nozzle Configurations of Scramjet Engine;Symmetry;2024-08-14

2. Numerical investigation of thermochemical non-equilibrium effects in Mach 10 scramjet nozzle;The Aeronautical Journal;2024-05-22

3. Multi-objective optimization design of scramjet nozzle based on grey wolf optimization algorithm and kernel extreme learning machine surrogate model;Physics of Fluids;2024-02-01

4. Maximum-Thrust Nozzle Based on Height Constraints;Aerospace;2023-11-21

5. Prospects for scramjet engines in reusable launch applications: A review;International Journal of Hydrogen Energy;2023-11

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