Results of flight tests are presented in which a helicopter rotor's blade surface pressure, leading edge stagnation point, surface flow magnitude and direction, and external noise were measured simultaneously. Aerodynamic instrumentation installed at five radial blade stations is described and unsteady aerodynamic phenomena observed on the blades are identified. Measured and theoretical normal force coefficients and angle of attack are compared. General agreement is found for the azimuthal variation of each parameter. Regions where theory and test disagree are identified and their importance to rotor performance design is discussed. Airload fluctuations and acoustic signals are used to locate and define the origin of rotor noise during high speed flight and in operating regimes of strong wake interaction. (Kursetz)
Helicopter rotor aerodynamic and aeroacoustic environments
Aerodynamisches and aeroakustisches Betriebsverhalten von Hubschrauberdrehfluegeln
AIAA-Papers ; 1-10
1977
10 Seiten, 14 Bilder, 1 Tabelle, 11 Quellen
Conference paper
English
Influence of Blade Aerodynamic Model on Prediction of Helicopter Rotor Aeroacoustic Signatures
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