Central Aerohydrodynamic Institute
RUS
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Wind tunnel T-106

Basic parameters

Flow Mach number 0.15–1.1
Reynolds number per 1 m up to 35*106
Total pressure 50–500 kPa
Dynamic pressure up to 58 kPa
Stagnation temperature 290–330 К
Angle of attack (α):
Electric-mechanical balance –10°–40°
In-model strain-gauge balance 0°–90°
Model dimensions:
Wing span up to 1.7 m
Length up to 2.2 m
Wing area up to 0.5 m2
Model weight up to 250 kg
Test section dimensions:
Cross section diameter 2.48 m
Test section length 4.85 m
Porosity coefficient of test section walls 15%

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General description

T-106 is a close-layout, continuous-operation, variable-density wind tunnel designed for investigating aerodynamic characteristics of aircraft models and flight vehicle components at subsonic and transonic velocities. The flow is generated by a compressor with an electric drive of 32 MW.

Test section with a circular cross-section and perforated walls is equipped with an electric-mechanical balance and a set of in-model strain-gauge balances for measuring aerodynamic forces and moments of models and their elements, and with supporting devices of 3 types (strip suspension, tail sting and under-fuselage strut).

The wind tunnel is equipped with automated computation and measurement complex for data monitoring, registration, acquisition, and processing during the experiment.



Capabilities

The following types of tests can be carried out in T-106:
  • electric-mechanical and strain-gauge balance measurements of total aerodynamic characteristics of aircraft models and their elements;
  • measurement of pressure distribution along the model surface using electronic pressure modules for 1000 points;
  • determination of characteristics of inlet models and aircraft models with the flow passing through the internal channels of thenacelles;
  • investigation of the models with simulation of the high-pressure jets (power plant nozzles, including those of variable thrust vector,jet flaps, etc.;
  • investigation of characteristics of aircraft models static and dynamic aeroelasticity;
  • test of half-models on a special supporting device;
  • investigation of wing profiles;
  • physical investigations.

Practical application

During 70 years T-106 has been one of the most loaded TsAGI’s facilities for investigating different-application flight vehicles at high subsonic and transonic velocities.