Numerical simulation of complex internal viscous flow in the hyshot-ii scramjet model

Chih-yung Wen; Chun Yueh Chen; Yen Sheng Chen

doi:10.2514/6.2011-2382

Numerical simulation of complex internal viscous flow in the hyshot-ii scramjet model

Chih-yung Wen, Chun Yueh Chen, Yen Sheng Chen

Research output: Chapter in book / Conference proceeding › Conference article published in proceeding or book › Academic research › peer-review

1 Citation (Scopus)

Abstract

This work describes the application of a cell-centered unstructured finite volume method with finite-rate chemistry model to hypersonic flows. The complex internal viscous flow in the HyShot-II Scramjet model is studied. Two dimensional CFD analyses considering air dissociation are presented on the complete geometry of the HyShot-II scramjet and separately on the combustion chamber at fuel-off conditions as a precursor to the future studies of three dimensional simulations, fuel-on combustion flows and designs of different scramjet models. The simulated pressure distribution in the combustor chamber at free stream flow of Mach 7.4 and altitude of 27 km is compared with the experimental results of a full-scale model of the HyShot II vehicle presented by Schramm et al1 conducted at the High Enthalpy Shock Tunnel (HEG), German Aerospace Center (DLR). Good agreement is observed between the wind tunnel test and CFD results.

Original language	English
Title of host publication	17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011
DOIs	https://doi.org/10.2514/6.2011-2382
Publication status	Published - 1 Dec 2011
Externally published	Yes
Event	17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011 - San Francisco, CA, United States Duration: 11 Apr 2011 → 14 Apr 2011

Conference

Conference	17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011
Country/Territory	United States
City	San Francisco, CA
Period	11/04/11 → 14/04/11

ASJC Scopus subject areas

Space and Planetary Science
Aerospace Engineering
Control and Systems Engineering

More information

10.2514/6.2011-2382

Cite this

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title = "Numerical simulation of complex internal viscous flow in the hyshot-ii scramjet model",

abstract = "This work describes the application of a cell-centered unstructured finite volume method with finite-rate chemistry model to hypersonic flows. The complex internal viscous flow in the HyShot-II Scramjet model is studied. Two dimensional CFD analyses considering air dissociation are presented on the complete geometry of the HyShot-II scramjet and separately on the combustion chamber at fuel-off conditions as a precursor to the future studies of three dimensional simulations, fuel-on combustion flows and designs of different scramjet models. The simulated pressure distribution in the combustor chamber at free stream flow of Mach 7.4 and altitude of 27 km is compared with the experimental results of a full-scale model of the HyShot II vehicle presented by Schramm et al1 conducted at the High Enthalpy Shock Tunnel (HEG), German Aerospace Center (DLR). Good agreement is observed between the wind tunnel test and CFD results.",

author = "Chih-yung Wen and Chen, {Chun Yueh} and Chen, {Yen Sheng}",

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Wen, C, Chen, CY & Chen, YS 2011, Numerical simulation of complex internal viscous flow in the hyshot-ii scramjet model. in 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011. 17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011, San Francisco, CA, United States, 11/04/11. https://doi.org/10.2514/6.2011-2382

Numerical simulation of complex internal viscous flow in the hyshot-ii scramjet model. / Wen, Chih-yung; Chen, Chun Yueh; Chen, Yen Sheng.
17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011. 2011.

Research output: Chapter in book / Conference proceeding › Conference article published in proceeding or book › Academic research › peer-review

TY - GEN

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N2 - This work describes the application of a cell-centered unstructured finite volume method with finite-rate chemistry model to hypersonic flows. The complex internal viscous flow in the HyShot-II Scramjet model is studied. Two dimensional CFD analyses considering air dissociation are presented on the complete geometry of the HyShot-II scramjet and separately on the combustion chamber at fuel-off conditions as a precursor to the future studies of three dimensional simulations, fuel-on combustion flows and designs of different scramjet models. The simulated pressure distribution in the combustor chamber at free stream flow of Mach 7.4 and altitude of 27 km is compared with the experimental results of a full-scale model of the HyShot II vehicle presented by Schramm et al1 conducted at the High Enthalpy Shock Tunnel (HEG), German Aerospace Center (DLR). Good agreement is observed between the wind tunnel test and CFD results.

AB - This work describes the application of a cell-centered unstructured finite volume method with finite-rate chemistry model to hypersonic flows. The complex internal viscous flow in the HyShot-II Scramjet model is studied. Two dimensional CFD analyses considering air dissociation are presented on the complete geometry of the HyShot-II scramjet and separately on the combustion chamber at fuel-off conditions as a precursor to the future studies of three dimensional simulations, fuel-on combustion flows and designs of different scramjet models. The simulated pressure distribution in the combustor chamber at free stream flow of Mach 7.4 and altitude of 27 km is compared with the experimental results of a full-scale model of the HyShot II vehicle presented by Schramm et al1 conducted at the High Enthalpy Shock Tunnel (HEG), German Aerospace Center (DLR). Good agreement is observed between the wind tunnel test and CFD results.

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Numerical simulation of complex internal viscous flow in the hyshot-ii scramjet model

Abstract

Conference

ASJC Scopus subject areas

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