Effects of NACA 65-blade's trailing edge modifications on the performance of a low-speed tube-axial fan

摘要

NACA 65-series airfoilsfeature a cusped trailing edge impractical for mass-production manufacturing processes. The effects of two different trailing edge modifications on NACA 65-810 blades on the performance of a low-speed rotor-only axial fan were investigated. Two rotors were realized and experimentally tested at two different tip leakage values. Experimental datawere compared each other and with results of CFD calculations performed on the ideal geometry. The comparison shows the performance losses of the actual geometriesagainst the ideal one. These losses must be taken into account when blade design is based on cascade data. Indications on the best modification strategy are also suggested.