Experimental Investigation of Flow Around a 3D Square Cylinder Using Five-hole Probe and Neural Networks Method

In the present research, axial compressor blade cascade was analyzed by using numerical and experimental methods. The model includes three rotor blades of an axial compressor having the same geometry and profile of NGTE 10C4/30C5 aligned parallel with a ratio of chord length to the blade pitch (rigidity) 0f 0.8-1.2. The experiments were done in a subsonic wind tunnel. Before the tests, some reforms in the output of the wind tunnel were designed to install a new test section, suitable for cascade testing. The necessary considerations are made to let a hot-wire probe to go through the wind tunnel’s wall move on the surface of the blades. The suction surfaces and pressure of the test blade have been equipped to the suitable tapping of the pressure to be connected through the connector hoses to the pressure transducers. Different situations between the blades were performed and at any stage of testing, the suction surface velocity and pressure profiles were measured in different longitudinal situations and distribution of surface pressure. Parallel with the experiments, the numerical analysis for different modes has been performed and the results were compared to experimental data. Combining the results of CFD and experimental measurements gives us a powerful tool for simulation, design and improvement.