Central Aerohydrodynamic Institute
RUS
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Wind tunnel T-128

Basic parameters

Flow Mach number 0.15–1.7
Reynolds number per 1 m up to 41*106
Total pressure 20–400 kPa
Dynamic pressure up to 80 kPa
Stagnation temperature 293–323K
Run duration continuous
Test section dimensions:
Cross section area 2.75 х 2.75 m
Test section length 12 m
Model dimensions:
Length up to 3 m
Wing span up to 2.2 m
Angle of attack (α) -30º -55º
Side slip angle(β) ±15 m

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General description

T-128 is a continuous-running, variable density wind tunnel designed for investigation of aircraft models at subsonic, transonic and supersonic velocities. The main compressor with electric drive of 100 MW generates the flow.

The wind tunnel is equipped with four interchangeable test sections, three of which have variable wall perforation (up to 128 independently controlled panels with perforation ratio varying from 0 to 18% according to the computer program). The fourth test section has slotted walls with porosity degree 0-14%.

The test sections are equipped with suspension systems of all the basic types (rigid strut with rear sting, strip suspension, model side wall mounting and half-model wall mounting), device for mounting “infinite span” wing and “swept” wing, and facility for staging investigation.
The wind tunnel is also equipped with a set of internal and external strain-gauge balances for measuring aerodynamic forces and moments of the models and their structural elements, automated computational system and control complex.



Capabilities

Transonic wind tunnel is designed to carry out the following experimental investigations:
  • determination of total aerodynamic characteristics of aircraft models and their elements
  • measurement of steady and unsteady pressure distribution on the model surface;
  • study of interference between the separating stages or cargo and carriers;
  • determination of characteristics of aircraft models with flow passing through the nacelle internal channels;
  • study of static and dynamic aeroelasticity characteristics of aircraft models;
  • experimental investigations of models (visualization of laminarturbulent transition, streamlining visualization by color oil materials and tufts, pressure sensitive paints).

Technological advantages

  • Adjustable perforation of the test section walls enables minimization of the flow boundary interference, increase in Re number due to
  • greater model size and increase in angle of attack range.
  • The accuracy of Mach number control in subsonic velocity range is ÄM = ? 0.001.
  • Interchangeable test sections with different suspension systems enable wide range of investigations.
  • Model preparation set is equipped with precision measurement system (accuracy degree is 0.003-0.03%).

Practical application

The above capabilities of the wind tunnel T-128 are widely used for investigating different models of airspace vehicles, rockets, civil and military aircraft of variuos purposes