Conventional Hypersonic Wind Tunnel

About Conventional Hypersonic Wind Tunnel

Marketing Overview

Our conventional hypersonic wind tunnel systems are developed from proven supersonic tunnel designs, enhanced with advanced high-temperature gas heating to enable stable hypersonic flow (Mach 5+). Designed for aerospace and defense research, these systems provide reliable simulation of extreme flight conditions for re-entry vehicles, missiles, and high-speed platforms.

Featuring intermittent blowdown operation, precision-contoured nozzles, and high-temperature-resistant components, the tunnel delivers accurate flow conditions for aerodynamic, thermal, and material studies. Flexible heating options and configurable test conditions ensure adaptability for a wide range of high-speed research applications.

Technical Datasheet (Generalized Ranges)

1. System Classification

• Mach Number Range: 5 14 (up to 2540+ with special gases)
• Flow Regime: Hypersonic
• Operation Type: Intermittent Blowdown (typical), Continuous (optional)

2. Test Section Specifications

• Type: Closed test section
• Shape: Circular / Square
• Typical Size: 0.1 m 1.5 m
• Length: 0.5 m 5 m

3. Flow Performance

• Velocity Range: ~1500 m/s 5000+ m/s
• Mach Number Control Accuracy: 0.02 0.1
• Flow Uniformity: 1% 2%
• Unit Reynolds Number: ~10 10 per meter (typical ~3 10/m with air)
• Test Duration: Milliseconds to a few seconds

4. Flow Generation System

• Type: Blowdown with vacuum-assisted exhaust
• Upstream Pressure: 10 bar 200+ bar
• Downstream System: Vacuum tank for enhanced pressure ratio

5. Thermal System (Key Feature)

• Purpose: Prevent gas liquefaction and simulate high-temperature flow
• Heating Methods & Typical Temperature Ranges:
• Gas combustion heater: up to ~750 K
• Nichrome resistance heater: up to ~1000 K
• Fe-Cr-Al resistance heater: up to ~1450 K
• Alumina pebble bed heater: up to ~1670 K
• Zirconia pebble bed heater: up to ~2500 K
• Tungsten heater (with nitrogen): up to ~2200 K
• Graphite resistance heater: up to ~2800 K

6. Nozzle System

• Type: Convergent-divergent (hypersonic nozzle)
• Design Options:
• Axisymmetric contoured nozzle (preferred)
• Conical nozzle (simpler, less uniform flow)
• Special Features:
• High expansion ratio
• Water-cooled throat (for Mach > 7)

7. Operating Conditions

• Test Gas: Air (standard), Helium / Nitrogen (optional)
• High Mach Capability with Helium:
• Up to Mach 25 (ambient)
• Up to Mach 40+ (heated conditions)

8. Key Components

• Settling chamber with heating system
• High-pressure storage system
• Hypersonic nozzle assembly
• Test section with thermal protection (optional)
• Supersonic/hypersonic diffuser
• Vacuum exhaust system

9. Instrumentation (Optional)

• High-frequency pressure sensors
• Force and moment balances
• Heat flux gauges
• Schlieren / shadowgraph systems
• High-speed imaging and DAQ systems

10. Applications

• Re-entry vehicle and missile testing
• Aerodynamic heating and thermal protection studies
• High-speed flow physics research
• Material ablation and erosion testing
• Aerospace and defence R&D

11. Optional Configurations

• High-temperature material testing setups
• Alternative test gases (helium, nitrogen)
• Advanced cooling systems (nozzle throat)
• Enhanced vacuum and pressure systems
• Extended Mach number capability

12. Customization Options

• Mach number range and test duration
• Heating method and temperature capability
• Test section size and geometry
• Pressure and vacuum system design
• Instrumentation and diagnostics