Non-steady flow field of two-dimensional supersonic nozzles
Abstract
The non-steady flow field of an impulsively started dimensional nozzle was investigated, using double exposure interferometry. Two straight nozzles, one with a sharp-edged throat and the other with a rounded throat, were inserted into a 60mm x 150mm cross sectional shock tube. Incident shock Mach numbers were 2.0 and 2.4 in air. Continuous monitoring of wave interactions, incident shock, secondary shock, Mach stem, and slip line, were carried out using a streak camera technique. Time-wise development of the density distribution of the whole flow field showed a detailed structure of the starting process and the wave interactions. The steady flow field upstream of secondary shock obtained by the experiment was compared with a numerical calculation using a finite difference method with a shock capturing procedure. Very good agreement between them was obtained. Double exposure holographic interferometry provides a useful tool for generating a gas dynamic data base for evaluation of numerical calculations.
- Publication:
-
NASA STI/Recon Technical Report N
- Pub Date:
- 1985
- Bibcode:
- 1985STIN...8622888A
- Keywords:
-
- Flow Distribution;
- Steady Flow;
- Streak Cameras;
- Streak Photography;
- Supersonic Nozzles;
- Finite Difference Theory;
- Shock Tubes;
- Wave Interaction;
- Fluid Mechanics and Heat Transfer