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INCAS Wind Tunnels (INCAS)
Hosting Legal Entity
Romanian National Institute for Aerospace Research
220, Iuliu Maniu Boulevard, National Institute for Aerospace Research "Elie Carafoli" - INCAS Bucharest, Bucharest, PO: 061126 (Romania)
Type Of RI
Coordinating Country
Scientific Description
The National Institute for Aerospace Research "Elie Carafoli" (INCAS) is the leading research establishment in aerospace sciences in Romania, with more than 60 years tradition in aerospace engineering, flow physics and applied aerodynamics, using state-of-the-art technologies and unique infrastructure of national strategic importance. INCAS has been involved in all major national aeronautical projects for civil and military areas.Reorganized in December 2008, INCAS has been repositioned as a research establishment, acting under public law as INCD, coordinated by ANCS - National Authority for Scientific Research. This transformation recovers the original position of INCAS as a successor of INCREST - National Institute for Scientific and Technological Creation before 1990 and follows almost 20 years of activity as a private company of the state.INCAS offers the usage of research infrastructures including trisonic and subsonic wind tunnels with state-of-the-art technology and outstanding competencies in major and niche areas for development at international scale.

RI Keywords
Pressure distributions, Moments measurement, Trisonic wind tunnel, Noise measurement, Forces measurements, Aerodynamic measurements, Flow visualizations, Subsonic wind tunnel
RI Category
Aerospace and aerodynamics research facilities
Civil Engineering Research Infrastructures
Scientific Domain
Engineering and Energy
Laser Visualizations
Aeroacoustics and Airframe Noise Evaluation

using 72 microphone matrix system

Flow Visualizations

using smoke, tufts and oil paints

Forces and Moments Measurement

using the external TEM balance

Pressure Distributions

using the existing classical and electronic scanning devices

Trisonic Wind Tunnel

• blowdown type • 1.2m x 1.2m test sections (3D) • Mach number range : 0.1 … 3.5 • Reynolds number up to 100 millions/m • Max test run duration : 90 sec. • Max pressure : 12 bar (settling chamber) • Interchangeable porous transonic test section • Variable porosity from 0.01% up to 9% • Interchangeable 3D/2D 0.48m x 1.2m test section • Active model/combustion capability • Sting mounted, internal balance ♦ TASK & TEM equipment ♦ home made systems • Side-wall, half model balance • Pressure measurements ♦ Digital scanning systems : 2x128 ports ♦ Dynamic pressure systems : 64 kulites • Mach control system • CTS system (closed loop) • 800 mm schlieren system • PIV under development • IR camera • ultra fast digital camera

Subsonic Wind Tunnel

• Atmospheric pressure, continuous type facility • Maximum speed : 110 m/s • 2.5m x 2.0m x 4m test section • Usual Reynolds number up to 1.5 million. Traditional closed circuit type Solid walls test section External 6 component pyramidal type balance ♦ Maximum normal load : 10.000 N (Lift) ♦ Accuracy : 0.02 % full scale, all axes ♦ Resolution : 0.002 % full scale, all axes ♦ Pitch motion : -25....+45 deg. @ 1...5 deg/sec ♦ Yaw motion : +/- 180 deg. @ 0.5...6 deg/sec • Standard pressure acquisition systems ♦ Digital scanning system: 256 ports ♦ Dynamic pressure capability: 56 kulites ♦ Boundary layers pressure measurements • New data acquisition technologies ♦ Hot film/wire measurements ♦ IR camera ♦ PIV system ♦ 3D dynamic deformation – fast cameras • Laser visualization systems • CTS system – open/closed loop operation • Aeroacoustics and airframe noise evaluation ♦ 72 microphone matrix system ♦ Beamforming technology ♦ Cross-corelation with dynamic pressure/kulites

Date of last update: 22/03/2017
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