Pseudo-Stationary Oblique Shock-Wave Reflection in Carbon Dioxide - Domains and Boundaries.
Abstract
Transition boundaries for a triatomic gas between various types of shock-wave reflection configurations--regular reflection (RR), single Mach reflection (SMR), complex Mach reflection (CMR), and double Mach reflection (DMR)--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, Ms, and the wedge angle, theta sub w. The resultant transition map in the Ms - theta sub w plane will be of value to future researchers in the field as an aid in designing their experiments. Excellent agreement was obtained between the transition boundary from CMR to DMR according to the criterion proposed by Ben-Dor & Glass that the flow downstream of the reflected shock should be sonic relative to the kink of the reflected shock for the transition to occur and the results of the present experiments. This fact will further confirm the validity of their criterion. The density contours of the flow fields were obtained by means of infinite-fringe interferograms, some of which, particularly those of CMR and DMR, were hitherto unavailable in the literature. They may prove valuable for comparison with the results of numerical simulation of the phenomena, which is currently the subject of intense research at various institutions.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1981
- Accession Number
- ADA108553
Entities
People
- Samon Ando
Organizations
- University of Toronto