Machine Calculation of Unsteady Mach Reflections and Prandtl-Meyer Supersonic Flows.
Abstract
A new finite difference method, which employs a transformation of coordinates, has been used to calculate the interaction of a traveling shock wave with a wedge. The steady flow counterparts to this problem, Prandtl-Meyer compressions and expansion, have also been solved with the new method. The results of the calculations are compared with the experimental data of Dewey (1972) for the unsteady case of Mach reflection over a wedge. The results of the calculations for steady Prandtl-Meyer expansions and compresions are compared with results obtained from exact theory. The calculations are noted to differ from the theoretically correct values by differences on the order of one percent for the pressure, velocity, density, and Mach number. (Author Modified Abstract)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1973
- Accession Number
- AD0756195
Entities
People
- J. J. Yagla
Organizations
- Naval Surface Warfare Center Dahlgren Division