Low-speed wind tunnel measurements

Low-speed windtunnel measurements:

Measurement of aerodynamic characteristics of 2D airfoils, 3D models (scale models of aircraft, cars, trains and other transport vehicles, their parts, etc.), full scale measurement of device/equipment which is exposed to wind such as aerials, radars, etc.:

  • Force measurement by means of internal and external multi-component strain-gauge balance
  • Pressure distribution measurement on model surfaces with pressure probes, thermo-cameras, etc.
  • Calibration and measurement of probes and their characteristics (static pressure and total pressure probes, directional probes, etc.)
  • Flow trajectory visualization and evaluation (PIV, helium bubbles, smoke, etc.), visual recordings with high-speed cameras
  • Use of equipment for earth surface simulation, model manipulators, etc.
  • Flow velocity measurement with hot wire anemometers, PIV

 

Equipment:

closed circuit atmospheric wind tunnel of continuous run (3m LSWT): 

Within the Large Infrastructure project (LM2011016), which was financially supported by the MYES ministry, the extensive modernization of the aerodynamic tunnel 3mLSWT in VZLÚ took place. In the course of two years, the power unit of aerodynamic tunnel was replaced; the measuring cabin reconstruction and a complete replacement of the control system were carried out. A cooling system of test airflow has been installed and innovation has taken place in the field of measuring technology.

Due to the extensive reconstruction a significant improvement in aerodynamic wind tunnel parameters has been achieved:

  • Tunnel can now be used to measure aerodynamic characteristics of scale models
  • Circular test section of 3 m dia x 3 m in length
  • Maximum flow velocity 80 m/s with cooling
  • Maximum flow velocity 90 m/s without cooling
  • Cooling system is able to maintain a constant temperature in the tunnel working section during measurement at a tolerance of + - 1 ° C
  • Max. deviation of local velocity from mean velocity less than 0.5 %
  • Characteristic turbulence intensity 0.3

open circuit atmospheric wind tunnel of continuous run (1.8m LSWT): 

  • Tunnel to measure scale models´ aerodynamic characteristics and probe calibration
  • Circular test section of 1.8 m dia x 1.75 m in length
  • Maximum velocity 55 m/s
  • Max. deviation of local velocity from mean velocity less than 0.5 %
  • Characteristic turbulence intensity 0.5 %
     

closed circuit atmospheric wind tunnel of continuous run (0.6 m LSWT): 

  • Tunnel for probe calibration
  • Circular test section 0.6 m dia
  • Maximum velocity 65 m/s
  • Max. deviation of local velocity from mean velocity less than 1%
  • Characteristic turbulence intensity 0.5%
     

Research projects:

  • HELIX – “Innovative aerodynamic high lift concepts (HELIX)“, (2001-2005, FP5 EU, project No. G4RD-CT-2001-00516)
  • CARD – “Contribution to Analysis of Rotor Hub Drug reduction“ (2009-2011, JU Clean Sky)
  • GREEN-WAKE – “Demonstration of LIDAR Based Wake Vortex Detection System Incorporating an Atmospheric Hazard Map“, (2008-2011, 7FP EU, project No. 213254)
  • Large Infrastructure – “Wind tunnels -  renovation and operation”, (2012-2016, MŠMT-VI, project č. LM2011016)
  • ESPOSA – “Efficient Systems and Propulsion for Small Aircraft”, WP2.3 Whirl Flutter (2011-2015, FP7 EU, project No. 284859)
  • AJT – “Advanced Wing for the AJT Aircraft “, (2012-2015, MPO – TIP4, project No. FR-TI4/603)
  • UHURA – “Unsteady High-Lift Aerodynamics -  Unsteady RANS Validation“, (2018-2021, EU Horizon 2020, project No. 769088)

 

cONTACT PERSON:

Doc. Ing. Zdeněk Pátek, CSc., Chief Aerodynamist of VZLU
tel: +420 225 115 124, e-mail: patek@vzlu.cz

 

REFERENCES:

  • Z. Pátek, Petr Vrchota, J. Cervinka: EXPERIMENTAL AND COMPUTATIONAL STUDY OF GROUND EFFECT ON AIRFOIL SECTION. ICAS 2016 - 30th Congress of the International Council of the Aeronautical Science, Daejeon, Korea; 09/2016
  • Pátek Z., Červinka J. , Vrchota P.: WIND TUNNEL AND CFD STUDY OF AIRFOIL WITH AIRBRAKE. 28TH CONGRESS OF THE INTERNATIONAL COUNCIL OF THE AERONAUTICAL SCIENCES, Brisbane, Australia; 09/2012
  • Marian Zabloudil, Zdeněk Pátek, Petr Vrchota: WIND TUNNEL INVESTIGATION OF FLOWFIELD ON THE FOWLER FLAP AND IN THE COVE USING PIV METHOD. 27TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES, Nice, France; 09/2010