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- W2025678045 abstract "Methods are presented for estimating some of the more fundamental design variables of single-rotor helicopters (tip speed, blade area, disk loading, and installed power) based on design requirements (speed, weight, fuselage drag, and design hover ceiling). The well-known constraints of advancing-blade compressibility and retreating-blade stall are incorporated into the estimation process, based on an empirical interpretation of rotor performance data from large-scale wind-tunnel tests. Engine performance data are presented and correlated with a simple model usable for preliminary design. When approximate results are required quickly, these methods may be more convenient to use and provide more insight than large digital computer programs." @default.
- W2025678045 created "2016-06-24" @default.
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- W2025678045 date "1986-06-16" @default.
- W2025678045 modified "2023-09-27" @default.
- W2025678045 title "Helicopter rotor and engine sizing for preliminary performance estimation" @default.
- W2025678045 cites W235299306 @default.
- W2025678045 doi "https://doi.org/10.2514/6.1986-1756" @default.
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