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Hypersonic Shock Tunnel
Hypersonic shock tunnel
The usage of vacuum based shock tunnels are coming into prominence because of theri mobility and operational convenience in collecting data. They supplement and comolement each other. This technology becoming popular with the advent of hypersonic tunnels required for space and aeronautical applications.
This is a facility for generating shock waves to study the aerodynamics of aerospace components. For example, it can be used to simulate and study the flow field around a spacecraft or ballistic missile during its re-entry into the earth's atmosphere. This facility can simulate simultaneously both the flight speed and stagnation temperatures associated with hypersonic vehicles.
The tunnel consists of a long shock tube, a conical nozzle and a dump tank. The shock tube is honed for a precision surface finish and evacuated using rotary vacuum pump systems. A dump tank is connected to the shock tube through a conical nozzle. After evacuation the driver section of the shock tube is filled with a mixture of gases at a pressure of 150 bar in order to burst the diaphragm and create shock waves in the test section where the samples are located.
Tunnel size . | 180 mm |
Pressure operating | 150 bar |
Dump tank size | 1500 mm dia x 5200 mm length |
Nozzle cone dimensions (D) | 180mm (D) at the entry 1000 mm at the exit |
Shock tube | 180 mm dia for 100 bar |
Driver tube | 180 mm dia for 150 bar |
High vacuum system for Dump tank | 24000 lit / sec speed for 10 -4 m.bar |
Total Length of tunnel | 23.16 m |
Maximum speed simulated | 10 Mach |
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Hypersonic shock tunnel
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