The PARC3D code was selected by the authors to analyze a variety of complex and high-speed flow configurations. Geometries considered for code validation include ramps and corner flows, which are characteristic of inlets and nozzles. Flows with Mach numbers of 3-14 were studied. Both two- and three-dimensional experimental data for shock-boundary-layer interaction were considered to validate the code. A detailed comparison of various flow parameters with available experimental data is presented; agreement between the solutions and the experimental data in terms of pitot pressure profiles, yaw-angle distributions, static pressures, and skin friction is found to be very good. In addition, two- and three-dimensional flow calculations were performed for a hypersonic nozzle. Comparison of the wall pressure results with the published solutions is made for the two-dimensional case.
Three-dimensional viscous flow computations of high area ratio nozzles for hypersonic propulsion
1991-02-01
Miscellaneous
No indication
English
Reactive and Viscous Flow in Hypersonic Nozzles
Online Contents | 1994
|Reactive and viscous flow in hypersonic nozzles
AIAA | 1994
|Reactive and viscous flow in hypersonic nozzles
Tema Archive | 1994
|