Hot-Shot Wind Tunnel

About Hot-Shot Wind Tunnel

Marketing Overview

Our hot-shot wind tunnel systems are advanced hypersonic test facilities that generate high-enthalpy flow using pulsed electric arc discharge. Designed for extended-duration hypersonic testing, these tunnels provide quasi-steady flow conditions significantly longer than traditional shock tunnels, enabling both steady and dynamic aerodynamic experiments.

With high-energy electrical heating, controlled gas expansion, and precise measurement systems, the facility supports comprehensive testing of aerodynamic forces, thermal loads, and propulsion systems. Ideal for aerospace and defense research, the system enables realistic simulation of hypersonic flight conditions, including ramjet and high-temperature flow studies.

Technical Datasheet (Generalized Ranges)

1. System Classification

• Flow Type: Arc-heated, impulse / quasi-steady
• Mach Number Range: 8 22
• Flow Regime: Hypersonic / High-enthalpy

2. Operating Principle

• Electrical energy stored in capacitors/inductors
• Arc discharge heats and compresses gas at constant volume
• Diaphragm rupture initiates expansion through nozzle
• Hypersonic flow generated in test section
• Flow discharged into vacuum system

3. Test Section Specifications

• Type: Closed or free-jet
• Typical Size: 0.05 m 1.0 m
• Test Duration: ~20 200 milliseconds (quasi-steady)

4. Flow Performance

• Velocity Range: ~2000 m/s 6000+ m/s
• Mach Number Control Accuracy: 0.05 0.2
• Reynolds Number (per meter):
  ~1 10 2 10
• Flow Uniformity: 1% 3%

5. Thermal & Energy System

• Arc Chamber Temperature: Up to ~3000 4000 K
• Energy Storage Methods:
• Capacitor banks: up to ~10 MJ
• Inductor systems: ~5 100 MJ
• Direct grid supply: ~10 MJ
• Test Gas Options: Air / Nitrogen (preferred to reduce contamination)

6. Operating Conditions

• Arc Chamber Pressure: High-pressure pulsed system
• Vacuum Requirement: High vacuum downstream (10 bar typical before test)
• Pressure/Temperature Variation: ~10% 50% lower than shock tunnels

7. Key Components

• Energy storage system (capacitor/inductor bank)
• Arc chamber with electrodes
• Diaphragm system
• Convergent-divergent nozzle
• Test section
• Diffuser and vacuum tank
• Control and discharge system

8. Measurement & Instrumentation

(Requires high-speed synchronized acquisition)

• Pressure transducers
• Heat flux sensors
• Force and moment balances
• High-speed data acquisition systems
• Optical diagnostics (Schlieren / imaging)

9. Key Features

• Longer test duration than shock tunnels
• Quasi-steady hypersonic flow
• Suitable for both static and dynamic testing
• Enables full angle-of-attack testing in a single run
• Supports propulsion testing (e.g., ramjet studies)

10. Applications

• Hypersonic vehicle aerodynamics
• Thermal protection and heating studies
• Dynamic stability and control testing
• Ramjet / scramjet engine testing
• High-temperature gas dynamics research

11. Technical Challenges & Solutions

• Material Ablation Control:
• Use of nitrogen test gas
• Optimized electrode and insulation design
• Contamination Reduction:
• Controlled arc temperature (< ~4000 K)
• Improved chamber materials and geometry

12. Optional Configurations

• High-energy arc systems
• Advanced contamination control design
• Specialized test gases (nitrogen, helium)
• Enhanced diagnostics for transient measurements

13. Customization Options

• Energy storage capacity (MJ range)
• Mach number and test duration
• Test section size and configuration
• Arc chamber design and materials
• Instrumentation and diagnostics