Design Method of a Modular Shape-Transition Nozzle for an Axisymmetric Scramjet-Powered Vehicle
Publication: Journal of Aerospace Engineering
Volume 36, Issue 4
Abstract
For a hypersonic vehicle powered by modular scramjet, integration of the airframe with the engine is critical to generating positive net thrust. In this study, a design method that combines the ideas of streamline tracing and trimming is generalized to design the modular shape-transition nozzle for integrating with the axisymmetric vehicle after-body. As an example, the design of a modular shape-transition nozzle with three modules for an axisymmetric vehicle is presented, and the computational fluid dynamics (CFD) approach is adopted to obtain the detailed flowfield and performance of the modular nozzle. Smooth expansion of the burner-exits gas along the flow direction is involved in the modular nozzle. The flow interactions between any two module exhausts, as well as the flow interaction of the modular jet with the external freestream, are all appearing at the trailing edge of the modular nozzle. Moreover, the modular nozzle produces a net thrust coefficient of 0.8536 and an integrated thrust coefficient of 0.7896 for the vehicle. The mixing of the modular nozzle jet with the freestream is enhanced with the trimming of the separate nozzle module, an approach which can reduce the infrared radiation signal.
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Data Availability Statement
Some or all data, models, or code that support the findings of this study are available from the corresponding author upon reasonable request.
Acknowledgments
We would like to acknowledge the support of NSFC (National Natural Science Foundation of China) on the contract numbers of 90916023, 11672346, as well as the support of 1912 Project on the contract numbers of 2019-JCJQ-DA-001-072, 2019-JCJQ-DA-001-073, 2019-JCJQ-DA-001-141, and the authors are grateful to the editors and reviewers.
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Published In
Journal of Aerospace Engineering
Volume 36 • Issue 4 • July 2023
Copyright
© 2023 American Society of Civil Engineers.
History
Received: Sep 25, 2020
Accepted: Feb 23, 2023
Published online: Apr 24, 2023
Published in print: Jul 1, 2023
Discussion open until: Sep 24, 2023
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