Supersonic Wind Tunnel With Schlieren Optics

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Supersonic Wind Tunnel With Schlieren Optics

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Supersonic Wind Tunnel With Schlieren Optics Specification

Power Source
AC Electric

Automation Grade
Semi-automatic

Core Components
Nozzle, Schlieren Optical System, Test Section, Air Pump, Control Panel, Diffuser, Convergent-Divergent Nozzle

Model No

Voltage
220-240 V Volt (v)

Measurement Range
Mach 0.5 to Mach 2.0

Capacity
Variable, typically up to Mach 2.0 airflow capabilities Pcs/hr

Feature
Highly Efficient

Temperature Range
Ambient to 80 C (approx.) Celsius (oC)

Frequency
50 Hz / 60 Hz Hertz (HZ)

Accuracy
100 % %

Equipment Materials
Stainless steel test section, high-quality alloy framework, optical grade glass for Schlieren system

Type
Supersonic Wind Tunnel with Schlieren Optics

Usage
Laboratory

Display Type
Analog & Digital (for pressure, temperature & optics alignment)

Dimension (L*W*H)
Approx. 2200 mm x 650 mm x 1100 mm Millimeter (mm)

Weight
Approx. 120-200 kg (varies with configuration) Kilograms (kg)

About Supersonic Wind Tunnel With Schlieren Optics

UPERSONIC WIND TUNNEL WITH SCHLIEREN OPTICS

Subsonic and supersonic flows behave differently. Thus for example, a contraction in cross-section of the flow at subsonic speed causes an increase in velocity, and at supersonic speed causes velocity to slow down. Understanding these fundamental phenomena of supersonic flows helps in the design of e.g. gas and steam turbines, jets or rockets.

open wind tunnel used to study the aerodynamic properties of various drag bodies at subsonic or supersonic flow.

A fan draws in air from the environment through the supersonic wind tunnel. There is a subsonic nozzle located at the air inlet, in which the intake air accelerates. The carefully designed contour of the subsonic nozzle with integrated flow straightener ensures a uniform velocity distribution with little turbulence in the subsequent measuring section. In the closed measuring section, the air is accelerated further and flows around a drag body (rocket, projectile, double wedge and wedge). Further down the supersonic wind tunnel, the air flow in slowed down in supersonic and subsonic diffusers and comes through a suction filter into the fan. Here, the air is compressed and then emitted back into the environment. A sound damper at the air outlet limits the sound level.

Interchangeable walls with different contours are used in the measuring section to generate flow velocities up to Mach 1,8.

The Schlieren optics supplied allow direct observation of the supersonic flow and the resulting shock fronts. Pressures are detected with sensors, transmitted directly to a PC via USB and analysed there using the software supplied. Additionally, the pressure is displayed on a manometer at the measuring point. The continuous method of operation means there is enough time available for observation and taking measurements.

The well-structured instructional material sets out the fundamentals and provides a stepby- step guide through the experiments.

Pressure curves in supersonic nozzles (Laval nozzle)
Pressure curves and losses in tunnel flows with Mach > 1
Observe shock waves in drag bodies using Schlieren optics
Determining the Mach number from the angle of the shock waves
Comparison of theory and experiment

Specification:

Investigation of pressure curves in supersonic flow
Visualisation of Mach lines and shock waves using Schlieren optics
Continuously operating, open supersonic wind tunnel, low pressure principle
Positive displacement fan with variable speed
Interchangeable walls in the measuring section produce velocities up to Mach 1,8
Drag bodies: rocket, projectile, double wedge and wedge
Manometer for displaying the pressure in the measurement point
Software for data acquisition (pressure measurement) via USB under Windows Vista or Windows 7

Technical Data:

Positive displacement fan, variable speed
Sound-dampened, max. 84dB(A)
Power consumption: 55kW

Supersonic wind tunnel:

Cross-section of the measuring section: 100x25mm
Interchangeable walls for measuring section 1 x straight contour: Ma<1
2 x Laval contours: Ma 1,4 and Ma 1,8

Schlieren optics:

Halogen lamp with 50 and 100W
2 adjustable parabolic mirrors
Adjustable slit diaphragm
Screen for Schlieren optics

Drag bodies:

Wedge, double wedge, projectile, rocket
Recommended ambient conditions: 40% rel. humidity at 25°C

Dimensions and Weight

L x W x H: 3600 x 825 x 1800mm (wind tunnel)
L x W x H: 1450 x 1600 x 1750mm (fan)
L x W x H: 1760 x 600 x 1450mm (Schlieren optics)
Weight: approx. 1750kg (total)

Advanced Schlieren Optical System

The integrated Z-type double pass Schlieren system employs precision 150 mm optical grade mirrors and an adjustable knife edge for enhanced visualization of supersonic flow features. The inclusion of LED or halogen illumination highlights subtle density gradients, making shockwave and boundary layer phenomena distinctly visible in real time.

Versatile & Modular Test Section

With a test section measuring 300 mm x 80 mm x 80 mm, this wind tunnel is engineered for adaptability, featuring easily interchangeable convergent-divergent nozzles to suit varied aerodynamic studies. The viewing window is crafted from impact-resistant laminar glass, ensuring safety during high-speed testing scenarios.

Seamless Control and Data Acquisition

A PLC-based automation system offers high-precision control and user-friendly operation. All key performance parameters, including pressure and temperature, are monitored via versatile digital and analog displays. Multi-point digital manometers and pressure taps ensure comprehensive measurement for research-grade accuracy.

FAQs of Supersonic Wind Tunnel With Schlieren Optics:

Q: How does the Schlieren optical system enhance flow visualization in this wind tunnel?

A: The Schlieren optical system employs a Z-type double pass configuration with optical grade mirrors and an adjustable knife edge to highlight variations in air density, enabling precise, real-time visualization of shockwaves and boundary layers during supersonic flow tests.

Q: What is the process of changing the nozzles for different Mach number simulations?

A: The wind tunnel is equipped with interchangeable convergent-divergent nozzles. Users can easily swap out nozzles to achieve specific Mach number conditions, typically ranging from Mach 0.5 to Mach 2.0, enabling tailored aerodynamic experiments.

Q: When should the high-intensity LED or halogen slit lamp be used as the lighting source?

A: The choice between high-intensity LED or halogen slit lamps depends on the visualization requirements and test subject. LEDs are ideal for low-heat, long-duration observations, whereas halogen lamps provide higher intensity light for capturing finer optical details in Schlieren imaging.

Q: Where can real-time shockwave or boundary layer visualization data be accessed?

A: Real-time visualization data can be digitally acquired via the integrated camera mount, which is compatible with most digital cameras. The PLC-based control system coordinates data flow to connected acquisition interfaces, ensuring efficient recording and analysis.

Q: What are the main benefits of using this supersonic wind tunnel in aerodynamic research laboratories?

A: This wind tunnel offers 100% accuracy in supersonic testing, compliance with international standards, high safety with impact-resistant materials, and versatile data acquisitionall of which support reliable aerodynamic research and instructional use in laboratories.

Q: How does the control system facilitate operational convenience during experiments?

A: The PLC-based controls with analog and digital displays enable precise adjustment of test variables, automated data logging, and user-friendly system management, thus enhancing experimental repeatability and overall workflow efficiency.

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