In this paper, the influence of the nose-tip temperature on hypersonic crossflow instability is experimentally investigated using infrared thermal imaging and high-frequency pulsating pressure sensors at Mach 6 for a 7° semi-cone angle of 6° angle of attack. The wall temperature ratio (ratio of nose-tip temperature to total incoming temperature) Tw/T0 varies between 0.6 and 1.3. The experimental results show that the transition position gradually moves toward the tail of the cone as Tw/T0 increases. Wavelet analysis reveals stationary crossflow vortices with wave numbers ranging from 30 to 50, and the maximum wave number decreases as Tw/T0 increases. The pressure sensors are then used to detect the traveling crossflow waves of 15–50 kHz and the high frequency mode of 100–450 kHz. The high frequency mode is considered to be the secondary instability of the traveling crossflow waves. An increase in Tw/T0 stabilizes the traveling crossflow waves while weakening the secondary instability. The results of bispectral analysis show that an increase in nose-tip temperature weakens both the self-interaction of the secondary instabilities and the interaction between the traveling crossflow waves and their secondary instabilities.
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