CFD and experimental study of multi-orifice synthetic jet cooling device
- Validation of preliminary results with the results conducted by NASA Langley Research Centre Workshop
- Analysis of flow pattern from multiple orifices and jet interaction within consecutive orifices
- Introduction of a swirling device to investigate the effect of swirling flow on the performance of the system
CFD study of plain flapped NACA 0012 airfoil subjected to different flap angles and Mach numbers
- The simulation process was validated with previously documented work of NASA Langley Research Center. (Link)
- k - omega shear stress transport (SST) model was used, as it yields best computational results according to Eleni et. al. (PDF)
- Flap angles were changed from 10 degree to 50 degree at 10 degree interval for every mach number. Coefficient of lift and drag (Cl and Cd)for each flap angles were observed.
