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Comparison of calculated and measured pressures on straight and swept-tip model rotor blades (1983)

Caughey, D. A. ; Tauber, M. E. ; Phillipe, J. J. ; [et al.]

In: CASI

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Publication Date: 2019-06-28

Description: Using 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.

Keywords: AERODYNAMICS

Type: NASA-TM-85872 , A-9584 , NAS 1.15:85872

Format: application/pdf

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