Abstract
0.73 and0.78.Measurements are acquiredat several radial locations inphase-locked mode, encompassing the blade length;specificdatapostprocessingisaimedatdeterminingtheaerodynamicforces,namely,thesectionalthrustand torque at each cross section. The evaluation of the pressure field is based on the integration of the Navier–Stokes equations with the experimental velocity fields expressed in a frame moving with the propeller blade. The approach returns the evaluation of the three-dimensional pressure field, in particular over the blade surface, considerably simplifyingthe flowvisualizationandanalysisinraisingpropellerstudies.Thevelocityandpressuredataarefurther integrated by means of a contour approach to yield the propeller thrust and torque, and compared to data directly derived from a multicomponent balance and from the engine power consumption. Nomenclature AS = cross-sectional area of model support, m 2 CP, CD = pressure and drag coefficients c = chord, m cmax = maximum chord, m D, D0 = drag of the propeller and of the model support, N dE, lS = diameter and length of the engine cowling, m dp = propeller diameter, m ds =i nfinitesimal surface element, m 2
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