Numerical Investigation of Aerodynamic and Aeroheating Characteristics of Blunted Cone and Wedge for High Mach Number Flow
Publication: Journal of Aerospace Engineering
Volume 35, Issue 6
Abstract
In this study, the impacts of the windward shape on the aerodynamic and aero-heating characteristics of supersonic vehicles were investigated using the blunted cone and blunted wedge models. Then, three-dimensional (3D) numerical simulations were performed under three different attack angles (0°, 10°, and 20°) with the Mach number of 10. The prediction accuracy of the adopted approach was validated against a published shock tunnel experiment. The numerical results suggested that the airflow structure, boundary layer parameters, aero-heating, and boundary layer transition were highly affected by the windward shape of supersonic vehicles. Under the same attack angle, the entropy layer thickness for the blunted wedge was found to be obviously greater than that of the blunted cone, whereas the detachment of windward shock waves for the blunted wedge was more obvious than that of the blunted cone. Moreover, the boundary layer parameters of both blunted cone and wedge were found to vary with the position in the flow direction. The commonly used constant assumption for the boundary layer parameters in engineering might be inaccurate and induce undesired errors. Furthermore, the boundary layer transition was found to more easily occur for a blunted wedge due to more significant instability in a streamwise direction. However, cross-flow instability might occur for a blunted cone under nonzero attack angles. In addition, the ratio of number of the blunted cone to that of the blunted wedge at downstream was inconsistent with the commonly used empirical value of 1.73, especially under large attack angles () because of variable-entropy effects and cross-flow on the blunted cone surface.
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Data Availability Statement
Some or all of the data, models, or code that support the findings of this study are available from the corresponding author on reasonable request.
Acknowledgments
This study is supported by the National Natural Science Foundation of China (Project ID: 52008025).
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Published In
Journal of Aerospace Engineering
Volume 35 • Issue 6 • November 2022
Copyright
© 2022 American Society of Civil Engineers.
History
Received: Dec 30, 2020
Accepted: Apr 8, 2022
Published online: Jul 23, 2022
Published in print: Nov 1, 2022
Discussion open until: Dec 23, 2022
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