Central Aerohydrodynamic Institute
RUS
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Wind tunnel T-107

Basic parameters

Flow M number 0.1 - 0.86
Re number per 1 m up to 14.5∙106
Total pressure atmospheric
Dynamic pressure up to 35 kPa
Stagnation temperature 280 - 323 K
Angle of attack (α) range −8° up to14.5°
Primary suspension arrow-like band suspension
Run duration continuous
Test section sizes:
Cross-Section diameter 2.7 m
Test section length 3.5 m
Tested object sizes:
Length up to 2.2 m
Wingspan up to 1.8 m
Wing area up to 0.5 m2
Weight up to 200 kg

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General description

T-107 Wind Tunnel is an atmospheric continuous operation closed-loop facility that is equipped with four-component electro-mechanical balance to measure the aerodynamic forces and moments that affect the model. The WT is assigned to research (by use of specialized fan testing device) the high-speed fans, aircraft models and their components aerodynamic characteristics.

Capabilities

T-107 WT provides the following experimental studies to be carried out:

  • Assessment of single fan and birotating coaxial fans aerodynamic characteristics by VP-107 Device;
  • Assessment of total models aerodynamic coefficients by mechanical balance and strain gage one;
  • Assessment of pressure distribution by drain ports;
  • Physical researches (method of kaolin covering, oil film etc.);
  • Other types of physical researches.
  • Technological advantages

    • The only test-bench in TsAGI assigned to test the high-speed fans (bi-rotary ones including) at cruising flight.
    • Low test-costs due to lower drive power and air-cooling.
    • Low level of flow initial vorticity.
    • Application of band suspension enables the minimal model geometry distortion.

    Practical application

    It is in T-107 WT where propulsions for such aircraft as Tu-95, An-22, An-70 and so on were enhanced. The total amount of cruising flight regimes tests within DREAM European FP7 was carried out in this WT. The thrust and moment characteristics of high-speed bi-rotary fans, the blades loads, blades strain, distribution of blade pressure, near-field blade noise and engine pylon influence were investigated. The helicopters profiles characteristics were studied.