Gen LI, Caihong SU

DOI Number: N/A

Conference number: HiSST-2024-265

Hypersonic crossflow transition was investigated for a Mach 6 flow over a swept plate with a swept angle of 45deg by solving the compressible three-dimensional Navier-Stokes equations. In order to obtain the transition process, the nonlinear evolution of a stationary crossflow vortex was first simulated. After it saturated, broad-spectrum wall perturbations were imposed through a slot to trigger transition. The results showed that both the Type-I and -III secondary modes are excited during the transition, which grow exponentially and independently due to secondary instability. Overall, the Type-I mode achieves the largest amplitude and dominates the transition. Furthermore, the amplitude of the most amplified secondary instability mode based on bi-global analysis is used to correlate the transition locations for DNS cases with four different wall perturbation amplitudes, spanning across four orders of magnitude.It was demonstrated that the amplitude criterion based on secondary instability well correlates the transition locations for the DNS cases, which validates the amplitude criterion based on secondary instability for crossflow transition prediction.

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In Categories: 1.Events, High-Speed Aerodynamics and Aerothermodynamics, HiSST 2024
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