Supersonic Wind Tunnel

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