Li Jiahao, Wang Liang, Zhao Rui, Sha Xinguo, Wang Yutang

DOI Number: N/A

Conference number: HiSST-2025-271

During near-space hypersonic flight, boundary-layer transition strongly affects the aerodynamic stability of reentry vehicles. In this study, the Fu–Wang transition model is applied to investigate the dynamic stability of a hypersonic blunt-cone vehicle under forced pitching oscillations. Numerical simulations are conducted to track the evolution of the transition location and its influence on aerodynamic loads and dynamic responses. Results show that vehicle stability deteriorates as the transition point moves upstream, with the most severe instability occurring when the transition coincides with the center of gravity. Parametric studies further reveal that oscillation amplitude and frequency exert non-monotonic effects on dynamic derivatives, governed by the interplay between viscous unsteadiness and added-mass contributions. These findings highlight the critical role of transition in dynamic stability prediction and provide guidance for transition-control strategies in hypersonic vehicle design.

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In Categories: 1.Events, 1.HiSST 2025, High-Speed Aerodynamics and Aerothermodynamics with application to hypersonic regimes
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