Boundary-layer stability analysis is performed by computational fluid dynamics simulation of experiments conducted in the Calspan-University at Buffalo Research Center Large Energy National Shock Tunnel in support of the first flight of the Hypersonic International Flight Research Experimentation program. From the laminar flow solutions, disturbances are calculated using the linear parabolized stability equations method and instability is quantified by integrating the resulting disturbance growth rates. Comparisons are made between the experimentally measured transition locations and the results of the parabolized stability equations analysis. The results show that for the cases tested, the e~N transition correlation works better than the commonly used Re_θ/M_e engineering criterion for predicting the onset of boundary-layer transition from laminar to turbulent flow.
展开▼
