Preliminary Integrated Design of Hypersonic Vehicle Configurations Including Inward-Turning Inlets
Publication: Journal of Aerospace Engineering
Volume 28, Issue 6
Abstract
A design method employed for preliminary integration of a hypersonic vehicle airframe configuration with its propulsion flow path is described. This method is primarily based on the integration of the variable cross section inward-turning inlet and the airframe. Three typical configurations include lifting body, sim-waverider, and semi-axisymmetric cone. Rectangular-to-circular, erose-to-circular, and sector-to-circular shape transition Busemann inlets are designed to integrate these three vehicle bodies, respectively. The results of numerical simulations show that the aerodynamic performance of these configurations, coupled with the propulsion flow path, inherits the characteristics of their original airframe shapes, such as the high lift/drag ratio of sim-waverider and the low-drag performance of semi-axisymmetric cone configuration. The computed results also demonstrate that the inward-turning inlets integrate smoothly with their respective vehicle airframes and that the design method is viable.
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Acknowledgments
This study was partly supported by a project funded by the Priority Academic Program Development of Jiangsu High Education Institutions (PAPD) and the grants from the National Nature Science Foundation of the People’s Republic of China (No. 90716013, 51476076).
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Published In
Journal of Aerospace Engineering
Volume 28 • Issue 6 • November 2015
Copyright
© 2014 American Society of Civil Engineers.
History
Received: Apr 9, 2014
Accepted: Nov 6, 2014
Published online: Dec 11, 2014
Discussion open until: May 11, 2015
Published in print: Nov 1, 2015
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