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