This study is the investigation of grooved circular jet ow experimentally and using computational uid dynamics (CFD). Experimental studies were conducted by using straight circular and grooved circular tubes in a multi-purpose low-range subsonic wind tunnel. Single channel hot wire anemometer was used in turbulence measurements. Numerical studies for the solution of jet ow were performed through FLUENT program (ANSYS 14.5).Jet ow proles at dierent velocities were formed by using the data generated at predetermined stations in the Re b ). These parameters were calculated with reference to jet radius and jet half width. Graphics formed by the generated non-dimensional data were compared to the previous studies.

In this study, an artificial neural networks model was established by using experimental measurement values at low speed subsonic wind tunnel of which length was 75 cm and experiment test section was 32 cm × 32 cm, and model results were compared with experimental values and then, the prediction was made for the unmeasured tunnel stream values. In the wind tunnel, when the jet velocity was 25 m/s, four tunnel velocities, 0, 5, 10, and 20 m/s were used. At the four measurement stations; x/D = 0.3, x/D = 12.5, x/D = 31.2, and x/D = 50, experimental measurements were made by using hot wire anemometer. Plain circular jet flows at x/D = 0.3 and x/D = 50 stations with average tunnel flow velocities of 7.5 m/s and 15 m/s were studied by using artificial neural networks. The data was obtained and evaluated by graphics.