An experimental exploratory study of laminar, transitional and turbulent boundary layers on a slender, sharp cone at zero incidence in hypervelocity flow was conducted in the shock tunnel T5, whose high operating pressure permits achieving the necessary high Reynolds numbers at high total enthalpy. Surface heat transfer rate and resonantly enhanced flow visualization were used to determine transition location and flow structure. Results suggest that the transition mechanism at the conditions tested is via the Tollmien–Schlichting instability, but since no detailed information about the noise spectrum in the facility is available, a definite conclusion is not possible. A strong, gas-dependent increase of the transition Reynolds number evaluated at the reference temperature on specific total enthalpy was observed. This effect increases monotonically with decreasing the dissociation energy of the gas.
Experiments in Fluids – Springer Journals
Published: Jan 20, 1997
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