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Unsteady blade-surface pressures on a large-scale advanced propeller: Prediction and dataAn unsteady 3-D Euler analysis technique is employed to compute the flow field 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 (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.
Document ID
19910002486
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Nallasamy, M.
(Sverdrup Technology, Inc., Brook Park OH., United States)
Groeneweg, J. F.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1990
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
E-5630
NASA-TM-103218
NAS 1.15:103218
Report Number: E-5630
Report Number: NASA-TM-103218
Report Number: NAS 1.15:103218
Meeting Information
Meeting: Joint Propulsion Conference
Location: Orlando, FL
Country: United States
Start Date: July 16, 1990
End Date: July 18, 1990
Sponsors: SAE, ASEE, AIAA, ASME
Accession Number
91N11799
Funding Number(s)
CONTRACT_GRANT: NAS3-24105
PROJECT: RTOP 505-62-4D
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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