CFD ANALYSIS OF THE EFFECT OF PARABOLIC TAPER DISTRIBUTION OF AN UNTWISTED HELICOPTER ROTOR BLADE

CFD ANALYSIS OF THE EFFECT OF PARABOLIC TAPER DISTRIBUTION OF AN UNTWISTED HELICOPTER ROTOR BLADE

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The effect of parabolic taper distribution along the span of a helicopter rotor blade is analyzed in terms COLD-PRO IMMUNE FORMULA of the rotor thrust, torque and Figure of Merit.Various maximum chord length values are investigated.The Reynolds Averaged Navier-Stokes computations are done using the FINE/Turbo flow solver developed by NUMECA International.The Spalart-Allmaras turbulence model is used to calculate the eddy viscosity.The baseline blade is selected as the Caradonna-Tung rotor blade.

Different blade shapes were generated by setting the maximum chord length at different spanwise locations for the same planform Rubber Display Key area as the baseline blade.Three optimum cases are observed: maximum Figure of Merit, maximum thrust for the baseline Figure of Merit and maximum Figure of Merit for the baseline thrust.Those optimum cases are noticed when the maximum chord length is 1.3 times the baseline blade chord length.