Prediction of Turbulent Heat Transfer and Pressure on Swept Leading Edges

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

“…As shown by many authors [25][26][27][28] PollÕs formula [14], based on the reference temperature T * , does not correctly predict heat transfer rates in hypersonic flow. In order to build a more reliable tool, an extensive review of available resources has been carried out [22][23][24][25][26][27][28]34,[36][37][38][39][40][41][42][43][44][45][46][47][48][49]. Only cases with Reynolds numbers clearly higher than the one corresponding to the transition completion have been selected in order to minimize the low Reynolds number effects on turbulence [50].…”

“…When the attachment line surface is free of significant defects transition occurs at much larger Reynolds number, but the threshold is at least a function of the local Mach number and of the wall to stagnation temperature ratio [21]. Following initial attempts of predicting turbulent attachment line heat transfer [22,23] the most significant contributions have been the ones proposed by Poll [14,24] in which correlations for transitional and turbulent regimes are built up as extension of low speed results. However, many authors have shown that PollÕs approach, although simple to implement, does not correctly predict heat transfer rates in hypersonic flow [25][26][27][28].…”