Boundary-layer stability analysis is performed by computational fluid dynamic simulation of experiments conducted in the National Aeronautics and Space Administration Langley Research Center 20-in. Mach 6 Air Tunnel in support of the first flight of the Hypersonic International Flight Research Experimentation program. From the laminar computational flow solutions, disturbances are calculated using the linear parabolized stability equations to obtain integrated disturbance growth rates. Comparisons are made between the experimentally observed transition locations and the results of the stability analysis. The stability results from the NASA Langley Research Center Air Tunnel are combined with previous work done for the Calspan University at Buffalo Research Center Large-Energy National Shock Tunnel to show excellent correlation between predicted and observed boundary-layer transition locations. Roughness calculations are also performed and a Reynolds number based on trip height is tabulated with experimental results.
Bibliographical noteFunding Information:
HIFiRE is a joint program of the U.S. Air Force Research Laboratory and the Australian Defence Science Technology Organisation (DSTO). The U.S. portion of the technical program is managed by the U.S. Air Force Research Laboratory Air Vehicles Directorate RBAA. This work was sponsored by Sandia National Laboratories Award no. 619327 and by the U.S. Air Force Office of Scientific Research under grant no. FA9550-04-1-0341. The views and conclusions contained herein are those of the authors and should not be interpreted as necessarily representing the official policies or endorsements, either expressed or implied, of the U.S. Air Force Office of Scientific Research, or the U.S. Government.