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- W2072021666 abstract "A momentum-integral technique was developed to calculate the laminar boundary layer on rotating airfoils. This technique was applied to a flat plate and an NACA 0012 airfoil at zero lift under steady rotation. Chordwise and spanwise velocity profiles, wall shear stresses, and separation lines are presented and are found to compare favorably with previous calculations using a finite-difference technique. Experimental velocity data were obtained on a hover stand using dual sensor hot wire probes. Chordwise and spanwise boundary-layer profiles are presented for an NACA 0012 airfoil at zero lift. Similar profiles were observed at various rotor speeds by scaling the ^-coordinate. The experimental profiles were found to be fuller than those predicted by momentum-integral calculations." @default.
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- W2072021666 date "1973-12-01" @default.
- W2072021666 modified "2023-09-26" @default.
- W2072021666 title "A Preliminary Analytical and Experimental Investigation of Helicopter Rotor Boundary Layers" @default.
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- W2072021666 doi "https://doi.org/10.2514/3.50666" @default.
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