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Supersonic Wind Tunnel

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MOQ : 1 Unit

Supersonic Wind Tunnel Specification

Equipment Type
Supersonic Wind Tunnel

Material
Stainless Steel, Glass, Aluminum

Processing Type
Dynamic Testing

Condition
New

Technology
Supersonic Aerodynamics

Dimension (L*W*H)
Customized or Standard Sizes Available

Power Mode
Electric

Voltage
380V / 440V

Power Consumption
8-15 kW

Pressure Output
0.1 to 1.5 MPa

Application
Aerospace, Research Institutes, Educational Demonstrations

Coating Type
Corrosion Resistant Coating

Accessories
Instrumentation, Data Acquisition System, Nozzle, Diffuser, Air Compressor

Mounting
Floor Mounted

Flow Visualization
Schlieren System Compatible

Usage Mode
Continuous & Intermittent

Chamber Construction
Leak-Proof Sealing

Installation Service
Available Upon Request

Maximum Airflow Rate
Up to 8 kg/s

Noise Level
Below 85 dB

Display Type
Digital Control Panel

Control System
Programmable Logic Controller (PLC)

Cooling System
Integrated Water Cooling (Optional)

Calibration
Factory Calibrated

Test Section Length
500 mm to 2 m

Test Section Diameter
Up to 300 mm

Safety Features
Pressure Relief Valve, Emergency Shutoff

About Supersonic Wind Tunnel

Marketing Overview

Our supersonic wind tunnel systems are engineered for advanced aerodynamic testing in high-speed flow regimes where compressibility and shock wave phenomena dominate. Utilizing precision-designed convergent-divergent (de Laval) nozzles, the system generates stable and uniform supersonic flow for accurate evaluation of aerospace models and high-speed components.

With configurable nozzle geometries (fixed, solid-block, or flexible) and efficient supersonic diffusers for pressure recovery, the system ensures optimal performance across a wide Mach range. Designed for research institutions, aerospace development, and defense applications, the tunnel supports detailed analysis of shock interactions, drag characteristics, and high-speed flow physics.

Technical Datasheet (Generalized Ranges)

1. System Classification

Mach Number Range: 1.5 4.5
Flow Regime: Supersonic

2. Test Section Specifications

Type: Closed test section (typical)
Shape: Rectangular / Square
Cross-Section Area: 0.01 m 5 m
Typical Size: 0.3 m 0.3 m up to 5 m 5 m
Length: 0.5 m 8 m

3. Flow Performance

Velocity Range: ~500 m/s 1500 m/s
Mach Number Control Accuracy: 0.01 0.05
Flow Uniformity: 1% or better
Turbulence Intensity: < 0.5%

4. Nozzle System

Type: Convergent-Divergent (de Laval nozzle)
Design Principle:
Flow velocity determined by area ratio (test section / throat)
Configurations:

Fixed nozzle
Solid-block (interchangeable contour blocks)
Flexible nozzle (adjustable contour plates)

Nozzle Geometry:
Axisymmetric or two-dimensional (planar side walls with contoured surfaces)

5. Supersonic Diffuser

Multi-stage diffuser with:

Contraction section
Second throat
Subsonic diffuser

Function:
Efficient pressure recovery and controlled transition from supersonic to subsonic flow via weak shock systems

6. Operating Conditions

Total Pressure Range: 2 bar 50+ bar
Total Temperature Range: Ambient to 800 K (higher with heating systems)
Reynolds Number: Up to 10 10 (higher with specialized systems)

7. Drive / Flow Generation

Type:

Blowdown (high-pressure storage)
Continuous (compressor-driven, less common)

Power Requirement:
500 kW 50 MW

8. Key Components

Settling chamber with flow conditioning
High-pressure air supply / storage system
Convergent-divergent nozzle assembly
Test section with optical access (optional)
Supersonic diffuser system
Control valves and pressure regulation system

9. Instrumentation (Optional)

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

10. Applications

Supersonic aircraft and missile testing
Nozzle and intake performance evaluation
Shock wave and boundary layer interaction studies
High-speed propulsion systems
Aerospace and defence R&D

11. Optional Configurations

Flexible nozzle systems for variable Mach operation
Tri-sonic wind tunnel (subsonic + transonic + supersonic)
Ludwig tube (high Reynolds number testing)
Cryogenic wind tunnel (independent Re and Mach control)
Heated flow systems

12. Customization Options

Mach number range and nozzle design
Test section dimensions
Pressure and temperature capability
Instrumentation and visualization systems
Continuous or blowdown operation

Advanced Aerodynamic Testing Capability

Engineered for rigorous performance, this supersonic wind tunnel accommodates various research and educational applications. Its customizable test section and precise control systems replicate high-speed airflow environments essential for testing aerodynamic components. Flow visualization compatibility enables detailed studies of shock waves and flow patterns.

Reliable Safety & Efficient Operation

The wind tunnel incorporates top-tier safety features, including pressure relief valves and emergency shutoff systems, ensuring operator protection during high-pressure tests. With both continuous and intermittent usage modes, the unit provides operational flexibility, while low-noise operation and efficient energy consumption make it suitable for institutional and industrial environments.

Flexible Installation & Comprehensive Support

Tailored to suit specific spatial or performance requirements, the wind tunnel offers both floor mounting and a selection between standard or custom dimensions. Factory calibration and installation services ensure seamless integration into research workflows, while durable materials and corrosion-resistant coatings guarantee long-term reliability.

FAQ's of Supersonic Wind Tunnel:

Q: How is the airflow rate controlled and monitored in the supersonic wind tunnel?

A: The airflow rate is precisely governed through a Programmable Logic Controller (PLC) system and monitored via a digital control panel, supporting rates up to 8 kg/s for consistent and reproducible testing conditions.

Q: What safety mechanisms are built into the wind tunnel for high-pressure operation?

A: The equipment includes a pressure relief valve and emergency shutoff switch to handle overpressure situations, ensuring safe operation during all dynamic testing procedures.

Q: When is integrated water cooling recommended for operation?

A: Integrated water cooling is optional and is recommended during extended test runs or when dealing with particularly high airflow or pressure levels to manage heat buildup in critical components efficiently.

Q: Where can this wind tunnel be installed, and are installation services provided?

A: The unit is floor-mounted and suitable for laboratories, aerospace research facilities, and academic institutions. Professional on-site installation is available upon request to ensure optimal setup.

Q: What are the main applications of the Supersonic Wind Tunnel?

A: Designed for aerospace, research institutes, and educational demonstrations, the wind tunnel is ideal for aerodynamic component testing, flow visualization experiments, and validation of dynamic testing techniques.

Q: How does the Schlieren system compatibility benefit test procedures?

A: Schlieren system compatibility allows for advanced flow visualization, enabling the study of shock waves, boundary layers, and fluid dynamics with high clarity, which enhances the analysis of aerodynamic phenomena.

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