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- W260881878 abstract "The wind tunnel performance of a 10-percent thick helicopter rotor section design by numerical optimization is presented. The model was tested at Mach number from 0.2 to 0.84 with Reynolds number ranging from 1,900,000 at Mach 0.2 to 4,000,000 at Mach numbers above 0.5. The airfoil section exhibited maximum lift coefficients greater than 1.3 at Mach numbers below 0.45 and a drag divergence Mach number of 0.82 for lift coefficients near 0. A moderate 'drag creep' is observed at low lift coefficients for Mach numbers greater than 0.6." @default.
- W260881878 created "2016-06-24" @default.
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- W260881878 date "1980-03-01" @default.
- W260881878 modified "2023-09-26" @default.
- W260881878 title "An experimental evaluation of a helicopter rotor section designed by numerical optimization" @default.
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