and

An unsteady, three-dimensional Euler analysis technique was used to compute the flowfield of an advanced propeller operating at an angle of attack. The predicted blade-pressure waveforms for an angular inflow of 3 ° were compared with wind tunnel data at two Mach numbers, 0.5 and 0.2. For an inflow Mach number of 0.5, the predicted pressure response is in fair agreement with data: the predicted phases of the waveforms are in close agreement with data, whereas the magnitudes are underpredicted. At the low Mach number of 0.2 (takeoff), the numerical solution shows the formation of a leading-edge vortex which is in qualitative agreement with measurements. However, the highly nonlinear pressure response measured on the blade suction surface is not captured in the present.inviscid analysis