Some practical issues in the computational design of airfoils for the helicopter main rotor blades | Zendy

Ivan Kostić | Zendy

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Some practical issues in the computational design of airfoils for the helicopter main rotor blades

Author(s) -

Ivan Kostić

Publication year - 2004

Publication title -

theoretical and applied mechanics

Language(s) - English

Resource type - Journals

SCImago Journal Rank - 0.279

H-Index - 6

eISSN - 2406-0925

pISSN - 1450-5584

DOI - 10.2298/tam0404281k

Subject(s) - airfoil , camber (aerodynamics) , pitching moment , trailing edge , aerodynamics , rotor (electric) , aerospace engineering , moment (physics) , helicopter rotor , lift coefficient , computer science , pressure coefficient , structural engineering , mechanical engineering , engineering , angle of attack , physics , mechanics , classical mechanics , turbulence , reynolds number

Very important requirement for the helicopter rotor airfoils is zero, or nearly zero moment coefficient about the aerodynamic center. Unlike the old technologies used for metal blades, modern production involving application of plastic composites has imposed the necessity of adding a flat tab extension to the blade trailing edge, thus changing the original airfoil shape. Using computer program TRANPRO, the author has developed and verified an algorithm for numerical analysis in this design stage, applied it on asymmetrical reflex camber airfoils, determined the influence of angular tab positioning on the moment coefficient value and redesigned some existing airfoils to include properly positioned tabs that satisfy very low moment coefficient requirement.

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