Unsteady blade surface pressures on a large-scale advanced propeller - Prediction and dataAn unsteady three dimensional Euler analysis technique is employed to compute the flowfield of an advanced propeller operating at an angle of attack. The predicted blade pressure waveforms are compared with wind tunnel data at two Mach numbers, 0.5 and 0.2. The inflow angle is three degrees. 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 while the magnitudes are underpredicted. At the low Mach number of 0.2 (take-off) 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.
Document ID
19900060165
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Nallasamy, M. (NASA Lewis Research Center; Sverdrup Technology, Inc. Brook Park, OH, United States)
Groeneweg, J. F. (NASA Lewis Research Center Cleveland, OH, United States)