Hypersonic Wind Tunnel

Hypersonic Wind Tunnel About

Marketing Overview

Our hypersonic wind tunnel systems are designed for cutting-edge aerodynamic research in extreme high-speed regimes (Mach 5 and above). Engineered to simulate realistic flight conditions for missiles, spacecraft, and re-entry vehicles, these tunnels enable precise analysis of high-temperature flow physics, shock interactions, and aerodynamic heating.

Utilizing advanced blowdown and vacuum-assisted flow generation, combined with high-temperature air heating systems, the tunnel delivers stable hypersonic flow conditions. Multiple configurationsincluding shock tunnels and hot-shot facilitiesallow flexibility for a wide range of experimental requirements, from force measurement to heat transfer and ablation studies.

Technical Datasheet (Generalized Ranges)

1. System Classification

• Mach Number Range: 5 15+ (higher on request)
• Flow Regime: Hypersonic

2. Test Section Specifications

• Type: Closed test section (typical)
• Shape: Circular / Square
• Cross-Section Area: 0.01 m 3 m
• Typical Diameter / Size: 0.1 m 2 m
• Length: 0.5 m 5 m

3. Flow Performance

• Velocity Range: ~1500 m/s 5000+ m/s
• Mach Number Control Accuracy: 0.02 0.1
• Flow Uniformity: 1% 2%
• Test Duration (Blowdown / Shock): Milliseconds to several seconds

 4. Flow Generation System

• Type:
• Blowdown with vacuum-assisted exhaust
• Shock tunnel / impulse facility
• Hot-shot / arc-heated systems
• Pressure Generation:
• Upstream high-pressure storage: 10 bar 200+ bar
• Downstream vacuum tank for enhanced pressure differential

5. Thermal Management

• Total Temperature Range: 300 K 3000+ K (depending on heating method)
• Heating Methods:
• Electrical heaters
• Combustion heating
• Arc heating (for very high temperatures)
• Purpose:
• Prevent gas liquefaction
• Simulate high-temperature flight conditions

6. Nozzle System

• Type: Convergent-Divergent (Hypersonic nozzle)
• Design: High expansion ratio for hypersonic flow
• Configuration: Fixed or interchangeable contour

7. Operating Conditions

• Reynolds Number: Up to 10 10 (higher with specialized systems)
• Flow Density: Wide range (including low-density simulation options)

8. Key Components

• Settling chamber with heating system
• High-pressure air storage system
• Hypersonic nozzle assembly
• Test section with thermal protection (optional)
• Vacuum tank / exhaust system
• Control valves and instrumentation

9. Instrumentation (Optional)

• High-frequency pressure sensors
• Force and moment balances
• Heat flux gauges
• Schlieren / shadowgraph systems
• High-speed imaging systems
• Data acquisition systems (DAQ)

10. Applications

• Missile and re-entry vehicle testing
• Spacecraft and satellite aerodynamics
• Thermal protection system (TPS) studies
• Aerodynamic heating and ablation analysis
• High-speed flow physics research

11. Optional Configurations

• Shock tunnel
• Low-density (rarefied flow) wind tunnel
• Hot-shot / arc-jet tunnel
• Light piston / gas piston tunnel
• Long-duration hypersonic facility

12. Customization Options

• Mach number range and test duration
• Test section size and geometry
• Heating method and temperature capability
• Pressure and vacuum system design
• Advanced diagnostics and instrumentation