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Shock Tunnel Specification

Equipment Type
Shock Tunnel Equipment

Material
Stainless Steel

Processing Type
Thermal Processing

Condition
New

Technology
Shock Tube Technology

Dimension (L*W*H)
Customizable as per client requirements

Power Mode
Electric

Voltage
220V / 380V

Power Consumption
Varies per application, generally 5-15 kW

Pressure Output
Up to several hundreds of bars (exact rating customizable)

Application
Used for high-speed aerodynamic testing and simulation of extreme atmospheric conditions

Coating Type
Anti-corrosive coating

Accessories
Comprehensive control panels, gas supply systems, pressure sensors

Data Logging
Integrated digital data acquisition system

Automation Grade
Semi-automatic to fully automatic available

Control System
Programmable logic controller (PLC) based operation

Temperature Range
Ambient to 5000 Kelvin

Visualization
Optical windows and high-speed camera compatibility

Maintenance Requirement
Low and modular for easy servicing

Noise Level
Less than 80 dB (during operation)

Test Chamber Material
High-grade stainless steel with reinforced construction

Installation Type
Floor-mounted

Test Medium
Air or inert gases

Ambient Temperature Tolerance
Up to 50C operating environment

Safety Features
Pressure relief valves, emergency shutoff switches, grounded enclosure

Minimum Order Quantity
1 unit

Drive Section Length
Customizable based on simulation needs

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

Advanced Testing for Extreme Conditions

This Shock Tunnel is meticulously engineered to replicate high-speed and high-pressure environments, supporting test mediums such as air and inert gases across a temperature spectrum from ambient to 5000 Kelvin. Its adaptability makes it valuable for aerospace, defense, and academic research, providing accurate simulation of extreme atmospheric events.

Reliable Construction and Safety

Built from high-grade stainless steel with reinforced and anti-corrosive features, the Shock Tunnel is designed for durability and safety. Key safety measures-including pressure relief valves, emergency shutoff switches, and a grounded enclosure-ensure operators are protected throughout every testing phase.

User-Friendly and Automated Operation

The Shock Tunnel's operation is governed by a programmable logic controller (PLC), with options ranging from semi-automatic to fully automatic usage. Maintenance requirements are low, with a modular design for efficient servicing. Compatible with digital data logging and visualization tools, the system's performance data is effortlessly managed and analyzed.

FAQ's of Shock Tunnel:

Q: How does the Shock Tunnel simulate extreme aerodynamic environments?

A: The Shock Tunnel uses advanced shock tube technology to simulate high-speed, high-pressure airflow by rapidly heating test mediums such as air or inert gases up to 5000 Kelvin, allowing for accurate replication of extreme atmospheric conditions observed in aerospace and defense applications.

Q: What are the primary applications of the Shock Tunnel equipment?

A: This equipment is primarily used for high-speed aerodynamic testing, thermal processing, and simulation of extreme environmental conditions. It is essential for research in aerospace, gas dynamics, and atmospheric science, as well as for the validation of material and design under simulated flight conditions.

Q: When should I choose a customizable drive section length?

A: A customizable drive section length is recommended when specific simulation requirements, such as unique pressure profiles or flow durations, are necessary for your experiments. This customization enhances the tunnel's suitability for a broad range of test scenarios.

Q: Where can the Shock Tunnel be installed and operated safely?

A: The Shock Tunnel is designed for floor-mounted installation in well-ventilated laboratory or industrial settings, with an ambient operating temperature tolerance up to 50C. Comprehensive safety features and noise levels below 80 dB make it suitable for research institutions and manufacturing environments alike.

Q: What is the process for visualizing test results in this Shock Tunnel?

A: Test visualization is supported through optical windows and compatibility with high-speed cameras. This allows real-time observation and detailed analysis of flow dynamics and thermal effects during testing, aiding in comprehensive experimental reporting.

Q: How does the integrated control system benefit daily operations?

A: The PLC-based control system automates and simplifies testing procedures, ensuring consistency and reducing manual intervention. Combined with digital data acquisition and logging, it streamlines operations and enables efficient monitoring and traceability of experiments.

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