Wind Tunnel
This product is a fundamental experimental platform for low-speed aerodynamics research, designed to study basic flow principles and verify related aerodynamic theories.
The wind tunnel consists of the test section (including silencer), drive system, and basic control system. Various models such as airfoils, aircraft configurations, and bluff bodies can be installed in the test section to investigate aerodynamic interactions, including lift, drag, pitching moment, and pressure distribution.
With optional modules such as the 32-channel pressure system, smoke generator, and three-component force balance, the system supports a wide range of aerodynamic theory verification and experimental research. Some modules support customization and extended experimental design.
The main unit is equipped with a touchscreen display system, integrating multiple aerodynamic model interfaces. It provides real-time data visualization, dynamic curve display, and Excel data export. In addition to standard aerodynamic models, the system can also function as a versatile data acquisition platform for extended aerodynamics research.
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Experimental Functions
1.Touchscreen interface with audio feedback for system control and configuration.
2.Built-in interfaces for wind tunnel model monitoring, three-component force balance display, and 32-channel pressure display, with real-time dynamic curves and Excel data export.
3.Supports full input/output control and data acquisition for all compatible modules.
4.Can serve as an extended data acquisition system for lift, drag, pitching moment, and pressure distribution measurements.
5.Study boundary layer effects and pressure distribution (requires 32-channel pressure system and boundary layer module).
6.Analyze friction drag of different bluff body shapes (requires three-component balance and 3D drag model).
7.Measure pressure distribution and lift characteristics of the NACA 0012 airfoil (requires 32-channel pressure system and airfoil model).
8.Study effects of flap deflection on lift, drag, and pitching moment of the NACA 2412 airfoil (requires force balance and airfoil module).
9.Measure aerodynamic forces on NACA 0012 wings with different spans (requires force balance and airfoil module).
10.Study lift, drag, and pitching moment characteristics of NACA 2415 high/low wing aircraft model (requires force balance and airfoil module).
11.Study aerodynamic characteristics of the S1210 airfoil model (requires force balance and airfoil module).
12.Demonstrate flow characteristics around various bluff bodies (requires smoke generator and corresponding models).
13.Conduct wake flow experiments and measure downstream pressure distribution (requires 32-channel pressure system, smoke generator, and models).
14.Provide stable, adjustable airflow for extended aerodynamics experiments.
Product Attributes
|
Product Model |
F130 |
Product Name |
Low-Speed Wind Tunnel |
|
Main Materials |
Galvanized steel sheet, stainless steel, 6061 aluminum alloy |
Dimensions |
4110 × 920 × 1910 mm |
|
Product Weight |
530 kg |
Operating Environment |
Room temperature, Relative humidity ≤ 85% |
|
Input Power Supply |
Three-phase five-wire system 380V ±5%, 50Hz |
||
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Required Modules |
● 2 sets of Pitot tube systems ● 1 electrical control cabinet |
Optional Modules |
● 32-channel pressure acquisition system ● Three-component force balance ● 3D drag model ● Flat plate boundary layer model ● NACA 0012 airfoil model ● High/low wing aircraft model ● Airfoil model kit ● Smoke generator |
Case Studies
Integrated Thermal Fluids and Energy Laboratory at Zhejiang University of Technology
Flight Demonstration Wind Tunnel at Shandong University
Multi Energy Complementary Experimental Platform at Hebei University
Statically Determinate Beam Section Internal Force Testing Apparatus Delivered to Jining Vocational and Technical College
Self Developed Compression Bar Stability and Stress Testing Apparatus Delivered to Shandong Polytechnic University
01
Integrated Thermal Fluids and Energy Laboratory at Zhejiang University of Technology
MicroNewton has equipped a five zone integrated teaching laboratory at Zhejiang University of Technology. The space covers heat transfer, thermodynamics, fluid mechanics, combustion, and multi energy systems with touchscreen stations for energy and power engineering programs.
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02
Flight Demonstration Wind Tunnel at Shandong University
MicroNewton has delivered a flight demonstration wind tunnel to Shandong University. Students operate a control stick to fly a NACA airfoil model in a subsonic flow, with a digital twin display showing lift, angle of attack, stall, and stability as they happen.
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03
Multi Energy Complementary Experimental Platform at Hebei University
MicroNewton has delivered an integrated multi energy complementary experimental platform to Hebei University of Engineering. The platform combines solar, wind, hydrogen, thermal storage, and heat pump training equipment in one source, storage, and load network for student laboratories.
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04
MicroNewton delivers self developed MST01 statically determinate beam section internal force testing apparatus to Jining Vocational and Technical College. This structural mechanics teaching equipment physically implements the section method to measure beam shear force and bending moment. It supports superposition principle verification and error analysis, suitable for civil engineering mechanical engineering and bridge related students at vocational and technical education institutions.
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05
MicroNewton self developed MS10 compression bar stability and stress testing apparatus has been delivered to Shandong Polytechnic University. This teaching device enables students to observe column buckling, measure critical load and verify Euler formula with configurable end supports. It serves civil engineering and mechanical engineering students, helping them distinguish strength failure from stability failure and compare real experimental data against theoretical material mechanics formulas.
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