Shock Tunnel

About Shock Tunnel

Marketing Overview

Our shock tunnel systems are designed for ultra-high-speed aerodynamic testing under extreme hypersonic conditions. By utilizing shock-wave compression to generate high-temperature, high-pressure test gas, the system produces realistic flight conditions for advanced aerospace applications.

Ideal for simulating re-entry environments, high-enthalpy flows, and real gas effects, the shock tunnel delivers precise data for heat transfer, pressure distribution, and aerodynamic forces. With millisecond-scale test durations and high-fidelity diagnostics, it is a critical tool for cutting-edge research in hypersonic aerodynamics and propulsion.

Technical Datasheet (Generalized Ranges)

1. System Classification

• Flow Type: Impulse / Shock-driven
• Mach Number Range: 5 25+
• Flow Regime: Hypersonic / High-enthalpy

2. Operating Principle

• Shock tube compresses test gas via shock waves
• Diaphragm rupture initiates flow
• High-temperature, high-pressure gas expands through nozzle
• Hypersonic flow generated in test section
• Flow duration limited by wave interactions and gas supply

3. Test Section Specifications

• Type: Closed or free-jet (typical)
• Typical Size: 0.05 m 1.5 m
• Test Duration: ~1 25 milliseconds

4. Flow Performance

• Velocity Capability: Up to ~6 7 km/s
• Mach Number Control: 0.05 0.2
• Reynolds Number: Up to 10 10
• Flow Uniformity: 1% 3% (short-duration flow)

5. Operating Conditions

• Driver Pressure: Up to ~3000 3500 bar (3000+ atm)
• Test Gas Temperature: Extremely high (high-enthalpy flow)
• Vacuum Requirement: High vacuum downstream

6. Key Components

• Driver section (high-pressure gas chamber)
• Shock tube (test gas section)
• Primary diaphragm (driver/test gas separation)
• Secondary diaphragm (nozzle isolation)
• Convergent-divergent nozzle
• Test section
• Vacuum tank and exhaust system

7. Tunnel Configurations

• Reflected shock tunnel (preferred for longer test times)
• Straight-through shock tunnel (shorter duration)

8. Instrumentation (Optional)

• High-frequency pressure transducers
• Heat flux gauges
• Force and moment balances
• Schlieren / shadowgraph imaging
• Spectroscopic and electron density diagnostics
• Ultra-fast data acquisition systems

9. Applications

• Hypersonic vehicle and re-entry simulation
• High-temperature real gas effects
• Thermal protection system (TPS) testing
• Shock wave and boundary layer interaction
• Plasma and ionization studies

10. Key Features

• Ultra-high enthalpy flow simulation
• Ability to replicate extreme flight conditions
• Short-duration, high-fidelity data capture
• Suitable for advanced aerospace and defence research

11. Optional Configurations

• High-enthalpy shock tunnels
• Plasma diagnostic integration
• Extended-duration reflected shock systems
• Custom nozzle geometries
• Specialized test gases

 12. Customization Options

• Mach number and velocity range
• Driver pressure capacity
• Test section size and configuration
• Diagnostic and measurement systems
• Vacuum and gas handling systems