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- W2365730710 abstract "This article introduces how a Mach number confirmed research rotor model tested with Z9 fuselage model in 8 m×6 m wind tunnel which is at Low Speed Institute of CARDC. It's the effect of sideslip angle on aerodynamic interactions between rotor/fuselage,rotor/horizontal tail and rotor/ vertical tail that is especially discussed. In low speed forward flight, the effect of sideslip angle on rotor/fuselage aerodynamic interactions is shown in all the six force components of the fuselage. It affects the fuselage pitching moment and horizontal tail force poorly, while the vertical tail force greatly. The curve of vertical tail force to sideslip angle has a good linearity." @default.
- W2365730710 created "2016-06-24" @default.
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- W2365730710 date "2002-01-01" @default.
- W2365730710 modified "2023-09-25" @default.
- W2365730710 title "Rotor/Fuselage Compound Model Wind Tunnel Test with Sideslip Angle" @default.
- W2365730710 hasPublicationYear "2002" @default.
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