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Subsonic Open Circuit Wind Tunnel

Subsonic Open Circuit Wind Tunnel

50000.00 - 500000.00 INR/Pack

Product Details:


Price And Quantity

  • 1 Pack
  • 50000.00 - 500000.00 INR/Pack

Trade Information

  • 10 Pack Per Month
  • 10-30 Days

Product Description

Sub Sonic Open Circuit Wind Tunnel:

The Sub Sonic Open Circuit Wind Tunnel is simple and safe in operation. It is supplied as a complete self-contained facility mounted on castors for ease of movement. Main equipment comprises the tunnel with a three-component balance system (lift, drag and pitching moment) and an air speed indicator. Air enters the test section through a carefully designed contraction followed by an aluminum honeycomb flow straightener designed to ensure that the flow is steady in both magnitude and direction and has a flat transverse velocity profile. A low angle diffuser at the outlet end contributes to flow stability in the test section. An axial flow fan is located at the outlet of the diffuser section. One number of floor mount 3 component balance for lift force, drag force and pitching moment measurement is installed in the test section.  


  • Lift force: 0 to 100 N, sensitivity ±0.01 N
  • Drag Force: 0 to 50 N, sensitivity ±0.01 N
  • Pitching Moment: 0 to 2.4 Nm, sensitivity ±0.001 Nm
  • 24 bit analogue to digital conversion of 3 strain gauge load cells for greater accuracy at low forces.  
  • Forces and moment data are digitally shown on LCD graphic display screen and are able to transfer to computer.  
  • Adjustment of pitch angle of models can be made with the tunnel in operation.  
  • The accuracy of the tunnel and its instrumentation make it suitable for undergraduate and simple research work.


Experimental Capability of Sub Sonic Open Circuit Wind Tunnel:


  1. Investigation of the development of the Boundary Layer on a flat plate by measurement of the total head distribution.  
  2. Measurement of pressure distribution around an aerofoil at various angles of attack.  
  3. Measurement of pressure distribution around a cylinder.
  4. Measurement of lift and drag on an aerofoil with leading edge slot and trailing edge flap.  
  5. Velocity and pressure distribution measurements using a Pitot static tube and yaw probe.  
  6. Measurement of drag for a selection of models of different shapes but common equatorial diameter.  
  7. Calibration of the Wind Tunnel velocity indicator using a Pitot static tube and inclined manometer.


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