Supersonic Combustion Wind Tunnel

About Supersonic Combustion Wind Tunnel

Short Marketing Overview

Our Supersonic Combustion Facility is a state-of-the-art, electrically heated high-speed wind tunnel designed for advanced research in supersonic and hypersonic combustion, including scramjet engine development. The system delivers clean, high-temperature airflow with precise control, enabling accurate simulation of real flight conditions without contamination from combustion byproducts.

With continuous flow capability, extended test durations, and advanced laser-based diagnostics, this facility provides unmatched insight into high-speed reacting flows, supporting both fundamental research and propulsion system development.

 

Technical Datasheet (Generalized Ranges)

Flow Performance

• Mach Number Range: 2 6 (expandable for hypersonic simulation)
• Velocity Range: ~1,500 3,000 mph (700 1,300 m/s)
• Flow Temperature: up to 2,0002,500 K (3,5004,500 F)
• Flow Medium: Clean air / vitiated air (CO, HO addition)

Operating Mode

• Type: Continuous flow (electrically heated)
• Test Duration:
• Steady-state: 30 minutes 2 hours
• Total run time (incl. thermal cycles): 3 8 hours

Heating System

• Heating Method: Electrical resistance heating
• Max Temperature Capability: up to ~2500 K
• Advantage: Non-vitiated flow (no combustion contaminants)

Test Section

• Configuration: Supersonic combustor test section
• Optical Access: Multi-side optical windows
• Application: Reacting flow and combustion diagnostics

Pressure & Flow Control

• Operating Pressure: 1 10 bar (typical)
• Mass Flow Control: Precision-controlled for combustion stability
• Flow Uniformity: High (optimized for combustion studies)

Diagnostics & Instrumentation

• Laser-Based Measurement Systems:
• Stereoscopic Particle Image Velocimetry (10 1000 Hz)
• Tunable Diode Laser Absorption Spectroscopy (TDLAS)
• Flow Visualization:
• High-speed Schlieren / shadowgraph (up to MHz range)
• Additional Measurements:
• Temperature, species concentration, velocity fields
• Pressure and heat release characteristics

Key Features

• Continuous operation for long-duration combustion studies
• Clean or controlled vitiated flow simulation capability
• High-temperature, high-speed reacting flow environment
• Advanced non-intrusive optical diagnostics
• Ideal for scramjet and high-speed propulsion research

Applications

• Supersonic combustion and scramjet engine development
• Hypersonic propulsion system validation
• High-speed reacting flow physics research
• CFD model validation and database generation
• Aerospace and defence propulsion programs

Advanced Flow Visualization Capability

This wind tunnel is equipped with Schlieren photography and shadowgraph systems for detailed analysis of supersonic and combustion flows. These features enable clear visualization of shockwaves, boundary layers, and combustion phenomena, which are crucial for research in aerospace propulsion and hypersonic aerodynamics.


Integrated Digital Data Acquisition and Control

The wind tunnel includes a modern, computer-integrated digital data acquisition system and PLC-based automated control panel. This setup ensures precise test execution, real-time monitoring, and easy adaptation to complex research protocols, allowing researchers to focus on analysis rather than setup.


Engineered for Safety and Compliance

Safety is prioritized through emergency stop, overpressure protection, and circuit breakers, ensuring secure operation for users. The tunnel adheres to ISO 9001:2015 quality standards and is CE certified, reflecting reliability and global regulatory compliance for demanding laboratory environments.