Shock and pressure amplification in a stepped Hartmann-Sprenger's tube
Abstract
A combined theoretical and experimental study was conducted to determine both pressure and shock amplification in a stepped Hartmann-Sprenger tube. The method of characteristics was employed to determine the flow dynamics and to construct the appropriate wave diagrams. Detailed pressure measurements were carried out up to diameter ratios of 4 and for a jet Mach number ranging between 0.4 and 1. Flow visualization inside the tube was obtained via spark schlieren photography taken at different time intervals during the resonant cycle. Experimental results were found to agree well with those obtained theoretically. Both theory and experiments show a decrease in the pressure amplitude's amplification with an increase in a jet Mach number. For sonic jets, and for large diameter ratios, the pressure amplitude was found to be 1.89 times that obtained from a constant area tube.
- Publication:
-
Canadian Aeronautics and Space Journal
- Pub Date:
- March 1988
- Bibcode:
- 1988CaASJ..34...48N
- Keywords:
-
- Flow Visualization;
- Hartmann Flow;
- Pipe Flow;
- Pressure Measurement;
- Shock Tubes;
- Wave Amplification;
- Computational Fluid Dynamics;
- Method Of Characteristics;
- Shock Wave Propagation;
- Fluid Mechanics and Heat Transfer