Transitional and turbulent heat transfer of swept cylinder attachment line in hypersonic flow

Abstract

A wide range of experimental results carried out in low enthalpy facilities is used to sustain simple correlations predicting heat transfer rates on an attachment line in hypersonic flow. It is observed that for long swept cylinders a nearly asymptotic state can be reached for which transition Reynolds number does not change substantially quite far from the apex of the cylinder. Intermittency based on measured heat fluxes was used to describe the laminar-turbulent process. Prediction of turbulent heat transfer rates is established using a reference temperature method that provides quick and relatively accurate estimates for a wide range of Mach number and temperature ratio.

An extended similarity theory applied to heated flows in complex geometries

“…The reference temperature method uses a fictitious reference temperature, T * R , that in a similar way is empirically determined under the condition that the theoretical results obtained for constant property calculations at this reference temperature represent the real situation for variable fluid properties (see, for example, Benard et al [2], Jayaraj et al [13] and Debrestian, Anderson [4]). The reference temperature is denoted in the form T *…”