Investigated topics:

1. Shock wave boundary - layer interaction

Shock induced separation, effect of humidity on incipient separation, wall curvature effect on separation flow structure, channel depth effect on the interaction.

2. Flow structure in the vicinity of a triple point

Measurement of stagnation pressure and static pressure traverses, determination of shock waves inclinations by visualization techniques.

3. Shock wave - boundary layer interaction control: passive, hybrid.

4. Modeling of the transpiration flow through perforated plates.

5. Transpiration flow through a perforated plate in a nozzle with the main stream at M = 0.3 - 1.1.

6. Helicopter impulse noise reduction.

7. Turbine cascade secondary flow analysis and methods of its control.

8. Cooling of gas turbine blades and endwalls.

9. Shock wave - boundary layer interaction control using streawise vortices, generated by air jets.

10. Streamwise vortex interaction with the horseshoe vortex.

11. CFD analysis of high lift tabs in a multi-element airfoils.

12. Unsteady shock wave behavior in a de'Laval nozzle.

13. Verification of phenomenologic description of the condensation phenomena by Molecular Dynamics numerical tools.

Schemat tunelu aerodynamicznego

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Charakterystyka:

• obieg zamknięty pojedynczy,
• zamknięta komora pomiarowa,
• stopień kontrakcji: 16.0,
• wymiary główne: długość 11m, wysokość 7m, szerokość 3m,
• kształt przekroju poprzecznego: ośmiokąt,
• współczynnik energii: 2.4,
• ruchome ściany dla zerowego gradientu ciśnienia.

 

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Przegląd urządzeń

16×PIII 600 MHz, 4×PIV Xeon 1.8 GHz, 2×PIV Xeon 2.6 GHz	12×P-III 1.13 GHz
128×P-III Xeon 700 MHz GALERA Cluster (one rack exposed)	8×R1000 195 MHz + 16×R12000 300 MHz SGI Origin 2000/Onyx 2 FREGATA mainframe

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