Qualitative investigation of cryogenic injected shock dissipation
Abstract
The injection of fluid nitrogen into the flow discharged from a two-dimensional, ambient, static-temperature and static pressure Mach = 2.7 nitrogen flow tunnel was observed. A bow shock stands approximately one diameter off the end of the 3.2 mm o.d. x 1.6 mm i.d. injection tube placed directly into the tunnel exhaust. Cryogenic injection creates a high density region in the injected region and within the bow shock wake but the standoff distance remains unchanged. However as the temperature reaches a critical value the sharp shock interface begins to fade resembling the density gradient seen at the interface of a supercritical fluid and the shock interface begins to move into the supersonic stream. As the injection temperature decreases, the interface continues to move into the supersonic stream and becomes more diffuse; the shock interface can not be distinguished. The phenomena is completely reversible.
- Publication:
-
NASA STI/Recon Technical Report N
- Pub Date:
- 1991
- Bibcode:
- 1991STIN...9129525H
- Keywords:
-
- Bow Waves;
- Cryogenics;
- Energy Dissipation;
- Gas Injection;
- Nitrogen;
- Shock Wave Propagation;
- Shock Waves;
- Gas Streams;
- Mach Number;
- Static Pressure;
- Supercritical Fluids;
- Supersonic Flow;
- Supersonic Speed;
- Wakes;
- Fluid Mechanics and Heat Transfer