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Comparison of calculated and measured pressures on straight and swept-tip model rotor bladesUsing the quasi-steady, full potential code, ROT22, pressures were calculated on straight and swept tip model helicopter rotor blades at advance ratios of 0.40 and 0.45, and into the transonic tip speed range. The calculated pressures were compared with values measured in the tip regions of the model blades. Good agreement was found over a wide range of azimuth angles when the shocks on the blade were not too strong. However, strong shocks persisted longer than predicted by ROT22 when the blade was in the second quadrant. Since the unsteady flow effects present at high advance ratios primarily affect shock waves, the underprediction of shock strengths is attributed to the simplifying, quasi-steady, assumption made in ROT22.
Document ID
19840008075
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Tauber, M. E. (NASA Ames Research Center Moffett Field, CA, United States)
Chang, I. C. (NASA Ames Research Center Moffett Field, CA, United States)
Caughey, D. A. (Cornell Univ. Ithaca, N.Y., United States)
Phillipe, J. J. (Office National d'Etudes et de Recherches Aerospatiales Paris, United States)
Date Acquired
September 4, 2013
Publication Date
December 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:85872
A-9584
NASA-TM-85872
Accession Number
84N16143
Funding Number(s)
PROJECT: RTOP 505-42-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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