High Speed Wind Tunnel

High Speed Wind Tunnel About

Marketing Overview

Our high-speed wind tunnel systems are designed for advanced aerodynamic research in subsonic, transonic, and supersonic regimes. Engineered for precision and reliability, these tunnels enable accurate simulation of high-speed flow conditions critical for aerospace, defense, and propulsion studies.

With configurable Mach number ranges, high-quality flow control, and advanced measurement integration, the system supports detailed analysis of shock waves, compressibility effects, and high-speed aerodynamic performance. Modular design and scalable power systems allow customization to meet diverse research and testing requirements.

Technical Datasheet (Generalized Ranges)

1. System Classification

• Mach Number Range: 0.4 4.5
• Categories:
• Subsonic: Mach 0.4 0.8
• Transonic: Mach 0.8 1.2
• Supersonic: Mach 1.2 4.5

2. Test Section Specifications

• Type: Closed (typical), Open (optional)
• Shape: Rectangular / Circular
• Cross-Section Area: 0.01 m 5 m
• Length: 0.5 m 10 m

3. Flow Performance

• Velocity Range: ~140 m/s 1500 m/s (depending on Mach number and conditions)
• Mach Number Control Accuracy: 0.01 0.05
• Flow Uniformity: 1% or better
• Turbulence Intensity: < 0.5%

4. Operating Conditions

• Total Pressure Range: 1 bar 50 bar (pressurized systems)
• Total Temperature Range: Ambient to 600 K (higher with heating systems)
• Reynolds Number: Up to 10 10+

5. Drive / Flow Generation

• Type:
• Continuous (compressor-driven)
• Intermittent (blowdown / storage tank type)
• Power Requirement:
  100 kW 50 MW (depending on scale)

6. Key Components

• Settling chamber with flow conditioning
• Convergent-divergent (de Laval) nozzle
• Test section (optical access optional)
• Diffuser and exhaust system
• High-pressure air supply / storage tanks
• Control valves and flow regulation system

7. Instrumentation (Optional)

• Pressure transducers and scanners
• Schlieren / shadowgraph systems (shock visualization)
• Force and moment balances
• High-speed data acquisition systems
• Temperature and density measurement

8. Applications

• Aerospace vehicle and missile testing
• Supersonic intake and nozzle studies
• Shock wave and compressibility research
• High-speed propulsion systems
• Academic and defence research

9. Optional Configurations

• Blowdown supersonic wind tunnel
• Hypersonic extension (above Mach 5, on request)
• Heated flow systems
• Variable-density / pressurized tunnels
• Optical access test sections

10. Customization Options

• Mach number range
• Test section size and geometry
• Pressure and temperature capabilities
• Instrumentation and visualization systems
• Continuous or intermittent operation

Advanced Digital Control and Data Acquisition

Utilizing a highly intuitive digital controller, users can achieve infinitely variable speed adjustments, enabling perfectly tailored airflow for a range of research scenarios. The integrated data acquisition system operates digitally and interfaces smoothly with computers and multiple sensors, allowing for seamless real-time monitoring and precise data collection.


Superior Performance and Flow Uniformity

This wind tunnel delivers exceptional flow uniformity (within 1%) across the entire test section, thanks to its expertly engineered axial flow fan and streamlined design. Capable of handling subsonic and supersonic regimes, it enables researchers and engineers to simulate real-world aerodynamic conditions and conduct rigorous analyses with confidence.


Rugged Construction and Safety Assured

Built from high-grade stainless steel, mild steel, and aluminum alloy, the wind tunnel boasts a powder-coated exterior for extra durability. Safety is enhanced by advanced features such as emergency stop, overload protection, and interlock mechanisms, ensuring a secure environment for both operators and sensitive experiments.