Wind tunnel T-113
Basic parameters
| Flow M number | 1.75…4.0 |
| Re number per 1 m | 26∙106…35∙106 |
| Total pressure | 186…687 kPa |
| Dynamic pressure | 50…78 kPa |
| Stagnation temperature | ambient |
| Run duration | not limited |
| Angles of attack range (α) | −4°…24° |
| Test section dimensions: | |
| Cross section area | 0.6 × 0.6 m |
| Length | 1.9 m |
| Model dimensions: | |
| Length | up to 0.6 m |
| Wing span | up to 0.36 m |
General description
T-113 WT is a high-supersonic blowdown strait-through facility with closed test section. The WT is equipped with two ejectors. The operational envelope is implemented by nine removable nozzles.
One ejector is used to realize М = 1.75...3.25. To reduce loads on model and suspension devices in the range of М = 1.75...4.0 the model may be tested with two powered ejectors under reduced total pressure P0 in settling chamber. The WT is equipped with four-component EM balances and a set of strain gage balances to measure forces and moments that act on tested models.
Capabilities
T-113 experimental capabilities allow to:
- Determine the total balance characteristics of aircraft models and their components;
- Determine the aircraft controls hinge moments;
- Measure the static pressure distribution over the aircraft model surface;
- Test half-wings and empennage models;
- Test infinite wing span models;
- Use flow field Schlieren visualization;
- Perform physical studies (laminar-turbulent transition visualization by China clay, PSP, etc.),
- Study the supersonic aircraft model near field for the sonic boom estimation.
Technological advantages
Suspension for infinite wing span models allows performing the full range of experimental research.
Practical application
T-113 WT is an experimental facility to test parametrically aircraft, rocket, and aerospace engineering models. In addition the T-112 capabilities are widely used for physical research.