Hypersonic boundary layer transitions over a yawed, blunt cone

• Published in: Aerospace science and technology Vol. 119; p. 107170
• Main Authors: Chen, J., Dong, S., Chen, X., Xu, G., Yuan, X.
• Format: Journal Article
• Language: English
• Published: Elsevier Masson SAS 01.12.2021
• Subjects: Blunt cone; Crossflow mode; Hypersonic transition; Streamwise vortex; Streamwise vortex; Blunt cone; Hypersonic transition; Crossflow mode
• ISSN: 1270-9638; 1626-3219
• DOI: 10.1016/j.ast.2021.107170

The boundary layer transition process for a straight circular cone with angle of attack (AoA) of 6° at Mach 6 was studied via high-resolution direct numerical simulations and stability analyses. A pair of strong streamwise vortices simultaneously induced a low-speed mushroom structure to emerge near the leeward plane. This structure was subject to low-frequency sinuous and high-frequency varicose instabilities. The transition between windward and leeward rays likely occurred due to the interactions between low-frequency traveling and stationary crossflow vortices. The lower-amplitude high-frequency secondary crossflow instability mode could be traced back to the upstream Mack mode. Although the axial and crossflow vortices were fundamentally different, there was a striking similarity between them since both high-frequency perturbations were driven by azimuthal shear and resulted in staggered positive and negative axial vortices along the streamwise direction.