Low Density Wind Tunnel

About Low Density Wind Tunnel

Marketing Overview

Our low-density wind tunnel systems are designed to simulate high-altitude, rarefied gas environments encountered by spacecraft and re-entry vehicles. Operating in slip and transition flow regimes, these tunnels enable precise investigation of aerodynamics where conventional continuum assumptions no longer apply.

With advanced vacuum systems, cryogenic or free-jet flow generation, and specialized non-contact measurement techniques, the system supports cutting-edge research in rarefied gas dynamics, high-altitude flight physics, and thermal behavior under low-density conditions. Optimized for low-pressure operation and high Knudsen number simulation, it is an essential tool for aerospace and space research.

Technical Datasheet (Generalized Ranges)

1. System Classification

• Flow Regime: Slip Flow & Transition Flow
• Mach Number Range: 5 20+
• Knudsen Number (Kn): ~0.01 10 (configurable for rarefied conditions)

2. Test Section Specifications

• Type: Free-jet or enclosed (low-density optimized)
• Typical Size: 0.01 m 0.5 m
• Test Region: Small, uniform rarefied flow core

3. Flow Performance

• Velocity Range: ~1500 m/s 6000+ m/s
• Flow Uniformity: 2% 5% (typical for rarefied flows)
• Reynolds Number: Very low (<< 10, depending on conditions)

 4. Operating Conditions

• Settling Chamber Pressure:
  ~0.001 bar 1 bar (significantly lower than conventional hypersonic tunnels)
• Vacuum Level (Test Section):
  Up to 10 10 bar
• Temperature Ratio (Model Surface / Stagnation):
  ~0.06 1

5. Flow Generation System

• Type:
• Blowdown with high-capacity vacuum pumping
• Free-jet expansion systems
• Nozzle Design:
• Cryogenic Laval nozzles
• Small orifice nozzles for rarefied flow generation

6. Key Features

• Large vacuum pumping and high sealing integrity
• Reduced model size and test density
• Specialized nozzle design for high Knudsen number flow
• Lower heating requirements compared to conventional hypersonic tunnels

7. Thermal System

• Heating Requirement: Moderate (to prevent liquefaction)
• Temperature Range: 300 K 1500 K (typical, depending on test gas and setup)

8. Measurement & Instrumentation

(Specialized due to low signal levels)

• Electromagnetic suspension balances (non-contact)
• Electron beam diagnostic systems
• Optical flow visualization techniques
• High-sensitivity pressure and heat flux sensors
• Advanced data acquisition systems

9. Applications

• High-altitude spacecraft aerodynamics
• Rarefied gas dynamics research
• Re-entry physics at low density
• Satellite and micro-scale vehicle testing
• Fundamental research in non-continuum flow

10. Optional Configurations

• Free-jet expansion tunnel
• Cryogenic nozzle systems
• Ultra-high vacuum systems
• Specialized diagnostic tools for rarefied flows

11. Customization Options

• Knudsen number range
• Vacuum system capacity
• Nozzle configuration and type
• Test section geometry
• Advanced non-contact instrumentation