Pseudo-stationary oblique shock-wave reflection in carbon dioxide: Domains and boundaries
Abstract
The transition boundaries for a triatomic gas between various types of shock-wave reflection configurations exhibited by a plane shock impinging on a compressive corner in a shock tube were studied experimentally using CO2 as the test gas. The shock Mach numbers ranged from 1.8 to 10.2, and the initial pressure from 3.5 to 80 torr at room temperature. The regions corresponding to the four types of reflection were obtained in terms of the shock Mach number M sub s and the wedge angle theta sub w. The resultant transition map in the M sub s minus theta sub w plane is presented. The transition boundaries are determined. The density contours of the flow fields were obtained by means of infinite-fringe interferograms. Shock-polar diagrams are analyzed. It is concluded that a perfect-gas model with an appropriate constant gamma should be used in determining the transition angles between various types of shock reflection for shock Mach numbers at least up to 10.
- Publication:
-
NASA STI/Recon Technical Report N
- Pub Date:
- April 1981
- Bibcode:
- 1981STIN...8210356A
- Keywords:
-
- Boundary Layer Transition;
- Shock Layers;
- Shock Waves;
- Wave Reflection;
- Carbon Dioxide;
- Density Distribution;
- Mach Number;
- Shock Simulators;
- Shock Wave Profiles;
- Fluid Mechanics and Heat Transfer