Mechmatics Engineering Private Limited

Specification :

• Wind Tunnel Acrylic Rectangular Test Section
• Traverse Mechanism
• Pitot Tube with Calibration
• U Tube Manometer with Stand (100 cm)
• Trolley

Wind tunnel is a facility for creating a uniform wind of known value in a test section where fluid flow phenomena can be investigated, models, of Aircrafts etc., can be tested from their performance, and also students training/teaching in fluid mechanics/aerodynamics. The facility can also be used for industrial aerodynamics testing and simulation studies on many of fluid problems.

The main part of the tunnel are Honey comb section, screens, contraction cone, test section, diffuser, safety screens, fan section, fan, motor and speed control drivers.
KEY SPECIFICATION
Computerised Data System Type of tunnel: Open circuit-suction type.Test section size: 0 - 1500 mm (As per Need)Maximum speed: 0- 50 m/secFan: Axial flow fan, Maximum rpm 1440Contraction Ratio: 9:1

The Wind tunnel was developed for experimentation and demonstration purposes in the fields of aerodynamics and fluid mechanics. It is a subsonic, open wind tunnel with a square measurement section profile. Overall length is 4.5 meters with 1 mtr test section. The extensive range of available accessories permits the performance of numerous experiments, e.g.:

• Methods of velocity measurement and Anemometry
• Determination of drag coefficients of different bodies (disc, sphere, streamlined object, aerofoil)
• Determination of drag and lift coefficients of aerofoils at different angles of attack
• Pressure distribution with flow around cylinders and aerofoils
• ExamFalling Sphere Viscometerination of boundary layers along flat plate

A wind tunnel essentially consists of the following:

• Prechamber with flow straightener
• Jet
• Measurement section
• Diffuser
• Fan

Funnel, jet and diffuser are made of MS. To provide access to the closed measurement section, the sliding guide permits adjustment of jet and funnel together with the measurement section. The flow straightener has a tubular honeycomb structure. The measurement section is made of perspex glass.The axial fan is provided with a downstream guide which makes it highly efficient and producing low noise. The fan is driven by an AC motor. A frequency converter or dimmer stat permits adjustment of rotational speed and thus air velocity. The fan is rigidly connected to the diffuser and both are attached to the laboratory trolley using rubber elements. This effectively provides shielding of vibrations and guarantees extremely smooth running. The switch box contains main switch, emergency stop, speed control and fan switch are located. A smoke generator is also provided

The inclined-tube manometer is used to indicate the current air speed at the entrance to the measurement section. The wind tunnel is installed on a laboratory trolley that is easy to move. The trolley is provided with shelves and lockable drawers for storing measuring instruments, models and other materials.

These balances are designed specifically for use in small to medium sized wind tunnels having cross sections of about 150 to 1200mm. The load sensing elements are high precision, strain gauged load cells with excellent repeatability and linearity characteristics and are temperature compensated for a temperature range of 0 to 60 C.
The geometrical construction of the load sensing systems allows the complete separation and independent measurement of the components of Lift, Pitch and Drag with negligible interactions of one component into another.

Load Ranges:
A combination of any of the three component load ranges shown may be incorporated at manufacture.
Component with Ranges

LIFT
0 – 90 / 120 / 180 / 240 N
DRAG
0 – 30 / 60 / 120 N

PITCHING MOMENT
0 – 2.5 / 5.0 / 10.0 Nm

The above figures are typical only as each balance is designed and manufactured to customer specific requirements. Different load ranges can usually be accommodated.

The six component Balance fits onto the working section of Subsonic Wind Tunnel. The six components Balance provides an easy-to-use support system for wind tunnel models. It measures lift, drag, side force, pitching moment, yawing and rolling moment exerted on the model. A mechanism constrains it to move in a plane parallel to the bottom plate only, while leaving it free to rotate about a horizontal axis. This arrangement provides the necessary three degrees of freedom. The forces acting on the model are transmitted by rods to six strain gauged load cells. The output from each load cell is taken via an amplifier to a PLC controlled display module. The display module mounts onto the wind tunnel control and instrumentation frame and includes a digital display to show the lift, drag and pitching moment directly.
Key Specifications

Measurement (Max Range)
Lift Force (0-50 kg) Drag Force (0-10 Kg) Pitching Moment (0-150 kg-cm) Side Force (0-6 kg) Yawing Moment (0-20 kg-cm) Rolling Moment (0-20 kg-cm)

Smoke Generator can be used to visualize air streamline characteristics on different surfaces. Part of supply includes   Control Panel;  Feed Bottle, fuel flow control pipe; Smoke Probe, flexible pipe, pipe connector, smoke probe holder

• Wind Tunnel Test Section from 150 mmm x 150mm upto 1500 mm x 1500 mm
• Mounting for various instrumentation
• Transperant Walls

The balance consists of the triangle platform connected to the rotating frame through the rods and pivot flexures. A wind tunnel model is connected to the triangle platform by two support struts: the main support strut and the tail support strut.

An optimized way of using 6 Load cell, which in turn uses change in resistance due to elongation which is measured in terms of voltage across that, can be recalibrated to the force applied. A set of forces at a distance causes couple thus even moments can be measured.

 

 

Overview

High-performance closed-circuit wind tunnels engineered for precision aerodynamic testing and energy-efficient operation. Built with robust steel construction, these systems offer complete design flexibility to accommodate space constraints, structural limitations, and specialized research requirements.

Designed primarily as single-return, horizontal circuits, each system delivers exceptionally stable, low-turbulence airflow suitable for advanced R&D and academic applications.

 

 

Key Advantages

• Ultra-Low Turbulence: Typically less than 0.10% across full speed range
• Energy Efficient: Lower power requirement vs. open-circuit tunnels
• Stable Flow Conditions: Isolated from ambient lab disturbances
• Low Noise Operation
• Clean Airflow: Dust and particulates contained within the circuit
• Enhanced Equipment Safety: Reduced risk to fan system

Technical Datasheet (Typical Ranges)

Performance

• Airspeed Range: 5 to 150 m/s (customizable based on design)
• Turbulence Intensity: < 0.10%
• Flow Uniformity: ±0.5% across test section

Circuit Configuration

• Type: Single-return (standard), multi-return/custom available
• Orientation: Horizontal (vertical/custom layouts optional)
• Construction: Heavy-duty steel fabrication

Test Section

• Size Range: 0.3 m × 0.3 m to 3 m × 3 m (customizable)
• Length: 1 m to 10 m
• Access: Modular panels, optical windows, instrumentation ports

Flow Conditioning

• Contraction Section:
  • Ratio: 6:1 to 12:1 (typical)
  • Profile: 5th or 9th order polynomial contour for smooth acceleration
• Settling Chamber: Multi-stage flow straightening and screening
• Diffusers & Corners: Optimized for minimal pressure loss

 

 

 

Design Considerations

Advantages vs Open Circuit

• Lower operating power for equivalent speeds
• Controlled environment for particulate or sensitive testing
• Minimal external airflow interference
• Reduced acoustic emissions

Limitations

• Higher capital cost (~2–3× for similar test section size)
• Larger installation footprint
• Heat buildup during extended operation
• Not ideal for combustion or exhaust-intensive testing

Customization Options

• Low-height or space-constrained layouts
• Integration around building columns/structures
• Thermal control systems (cooling/heat exchangers)
• Advanced instrumentation & automation
• Specialized test sections (aeroacoustics, automotive, UAV, etc.)

Applications

• Aerospace and automotive aerodynamics
• High-precision research and calibration
• Environmental and flow physics studies

Academic laboratories and national research centres

Flow Straightner with Settling chambers for wind tunnels
L/D Ratio as per standards
Avaialble in Square, Round, Hexagon and rectangular fashion
Sturdy ribs for mounting in ducts

Marketing Overview

Our Hypersonic Wind Tunnel systems are designed for cutting-edge aerodynamic research in extreme high-speed regimes (Mach 5 and above). Engineered to simulate realistic flight conditions for missiles, spacecraft, and re-entry vehicles, these tunnels enable precise analysis of high-temperature flow physics, shock interactions, and aerodynamic heating.

Utilizing advanced blowdown and vacuum-assisted flow generation, combined with high-temperature air heating systems, the tunnel delivers stable hypersonic flow conditions. Multiple configurations—including shock tunnels and hot-shot facilities—allow flexibility for a wide range of experimental requirements, from force measurement to heat transfer and ablation studies.

Technical Datasheet (Generalized Ranges)

1. System Classification

• Mach Number Range: 5 – 15+ (higher on request)
• Flow Regime: Hypersonic

2. Test Section Specifications

• Type: Closed test section (typical)
• Shape: Circular / Square
• Cross-Section Area: 0.01 m² – 3 m²
• Typical Diameter / Size: 0.1 m – 2 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%
• Test Duration (Blowdown / Shock): Milliseconds to several seconds

 

 

 

4. Flow Generation System

• Type:
  • Blowdown with vacuum-assisted exhaust
  • Shock tunnel / impulse facility
  • Hot-shot / arc-heated systems
• Pressure Generation:
  • Upstream high-pressure storage: 10 bar – 200+ bar
  • Downstream vacuum tank for enhanced pressure differential

5. Thermal Management

• Total Temperature Range: 300 K – 3000+ K (depending on heating method)
• Heating Methods:
  • Electrical heaters
  • Combustion heating
  • Arc heating (for very high temperatures)
• Purpose:
  • Prevent gas liquefaction
  • Simulate high-temperature flight conditions

7. Operating Conditions

• Reynolds Number: Up to 10⁶ – 10⁸ (higher with specialized systems)
• Flow Density: Wide range (including low-density simulation options)

8. Key Components

• Settling chamber with heating system
• High-pressure air storage system
• Hypersonic nozzle assembly
• Test section with thermal protection (optional)
• Vacuum tank / exhaust system
• Control valves and instrumentation

 

The axial and lateral turbulence are reduced and smooth flow of air entering the test section is achieved by installing the honeycomb and screens for most efficiency and efficiencies of the air inlet. The ratio of length to wall size of the honey comb is maintained as per the recommended standards. The wire mesh is also fixed to smoother the flow further. This is particularly, useful for obtaining laminar flow. The duct is secured to the test section by flange. The provision is also made for easy removal of diffuser and diffuser for possible separation from the test section, when required. It is also highly smothered and painted.

Marketing Overview

Our supersonic wind tunnel systems are engineered for advanced aerodynamic testing in high-speed flow regimes where compressibility and shock wave phenomena dominate. Utilizing precision-designed convergent-divergent (de Laval) nozzles, the system generates stable and uniform supersonic flow for accurate evaluation of aerospace models and high-speed components.

With configurable nozzle geometries (fixed, solid-block, or flexible) and efficient supersonic diffusers for pressure recovery, the system ensures optimal performance across a wide Mach range. Designed for research institutions, aerospace development, and defense applications, the tunnel supports detailed analysis of shock interactions, drag characteristics, and high-speed flow physics.

Technical Datasheet (Generalized Ranges)

1. System Classification

• Mach Number Range: 1.5 – 4.5
• Flow Regime: Supersonic

2. Test Section Specifications

• Type: Closed test section (typical)
• Shape: Rectangular / Square
• Cross-Section Area: 0.01 m² – 5 m²
• Typical Size: 0.3 m × 0.3 m up to 5 m × 5 m
• Length: 0.5 m – 8 m

3. Flow Performance

• Velocity Range: ~500 m/s – 1500 m/s
• Mach Number Control Accuracy: ±0.01 – ±0.05
• Flow Uniformity: ±1% or better
• Turbulence Intensity: < 0.5%

4. Nozzle System

• Type: Convergent-Divergent (de Laval nozzle)
• Design Principle:
  Flow velocity determined by area ratio (test section / throat)
• Configurations:
  • Fixed nozzle
  • Solid-block (interchangeable contour blocks)
  • Flexible nozzle (adjustable contour plates)
• Nozzle Geometry:
  Axisymmetric or two-dimensional (planar side walls with contoured surfaces)

5. Supersonic Diffuser

• Multi-stage diffuser with:
  • Contraction section
  • Second throat
  • Subsonic diffuser
• Function:
  Efficient pressure recovery and controlled transition from supersonic to subsonic flow via weak shock systems

6. Operating Conditions

• Total Pressure Range: 2 bar – 50+ bar
• Total Temperature Range: Ambient to 800 K (higher with heating systems)
• Reynolds Number: Up to 10⁷ – 10⁹ (higher with specialized systems)

7. Drive / Flow Generation

• Type:
  • Blowdown (high-pressure storage)
  • Continuous (compressor-driven, less common)
• Power Requirement:
  500 kW – 50 MW

 

 

8. Key Components

• Settling chamber with flow conditioning
• High-pressure air supply / storage system
• Convergent-divergent nozzle assembly
• Test section with optical access (optional)
• Supersonic diffuser system
• Control valves and pressure regulation system

 

Designed for precision aerodynamic testing, our high-speed open-circuit wind tunnels deliver exceptionally smooth, low-turbulence airflow for research, development, and educational applications. The open-loop design draws air directly from the laboratory environment, ensuring flexible installation and cost-effective operation without recirculation complexity.

Engineered for adaptability, these systems can be configured to suit constrained spaces such as low ceilings, narrow access points, or facilities with structural obstructions. From compact laboratory units to large-scale research tunnels, we offer both standard models and fully customized solutions.

Key Features

• Open circuit (non-recirculating) airflow design
• Ultra-low turbulence for high-precision measurements
• Modular construction for easy installation in restricted spaces
• Customizable geometry, speed, and test section size
• Expandable flow conditioning system

Standard Test Section Sizes

• 150 × 150 mm (6″ × 6″)
• 300 × 300 mm (12″ × 12″)
• 450 × 450 mm (18″ × 18″)
• 600 × 600 mm (24″ × 24″)
• 750 × 750 mm (30″ × 30″)

Custom sizes: up to 1000 × 1000 mm (40″ × 40″) and beyond

Technical Datasheet (Typical Ranges)

Airflow & Performance

• Airspeed range: 5 – 120 m/s (application dependent)
• Turbulence intensity: ≤ 0.25% (typical, with standard flow conditioning)
• Flow uniformity: ±0.5 – 1% across test section

Contraction Section

• Contraction ratio: 6:1 – 12:1 (standard ~9:1)
• Profile design: 5th- or 9th-order polynomial contour

Flow Conditioning

• Honeycomb straightener:
  • Material: Aluminium
  • Cell diameter: 3 – 10 mm
  • Length-to-diameter ratio: 6:1 – 10:1

·         Turbulence screens:

•  
  • Standard: 2 stainless steel screens
  • Expandable: up to 4 screens

 

Construction & Layout

• Frame: Modular steel/aluminium structure
• Test section: Clear acrylic or glass (optional)
• Installation: Custom-fit for lab constraints

Applications

• Aerodynamic research & validation
• Automotive and UAV testing
• Civil and structural wind studies
• Academic and educational labs