Design Methodology for Selecting a Single Expansion Ramp Nozzle Geometry that can Complete a Mission between Machs 3 and 7-Reference-Cited by-同舟云学术

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Design Methodology for Selecting a Single Expansion Ramp Nozzle Geometry that can Complete a Mission between Machs 3 and 7

Published:2023-05-27 Issue: Volume: Page:
ISSN:
Container-title:25th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
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Author:

Cerantola David¹,Gagnon Joel¹,Handford Dan¹,Dass Pradeep¹

Affiliation:

1. Space Engine Systems

Publisher

American Institute of Aeronautics and Astronautics

Link

https://arc.aiaa.org/doi/pdf/10.2514/6.2023-3052

Reference26 articles.

1. Propulsion Aspects of Hypersonic Turbo-Ramjet-Engines With Special Emphasis on Nozzle/Aftbody Integration

2. de Magalhães, J. F. S. C. "Design of a Single Expansion Ramp Nozzle and Numerical Investigation of Operation at OverExpandedConditions,"Ph.D.thesis,UniversidadedaBeiraInterior(Portugal),2021.

3. Carboni,J.D.,Shyne,R.J.,Leavitt,L.D.,Taylor,J.G.,andLamb,M."Supersonicinvestigationoftwodimensionalhypersonic exhaustnozzles," NASATM105687,1992. URLhttps://ntrs.nasa.gov/citations/19930006153.

4. Parametric Optimization of Single Expansion Ramp Nozzle (SERN)

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