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• W4313444133 abstract "It is very important for calculating aerodynamic load and strength design to obtain aerodynamic force of aircraft components accurately. The aerodynamic force of horizontal tail is usually obtained by means of component disassembly in wind tunnel test, That is, subtract the value of non horizontal tail configuration from the value of whole plane configuration to obtain the value of horizontal tail. Using CFD method, through the comparative study of component disassembly method and direct measurement results, it is found that for low Horizontal tail aircraft, the slope of Horizontal tail lift line obtained by component disassembly method is more than 25%. The main reason for the error is that the component disassembly method assumes that the aerodynamic characteristics of the wing and fuselage with/without Horizontal tail configuration remain unchanged, so the interference data of the whole plane Horizontal tail on the fuselage and wing are accumulated on the Horizontal tail components. The error change of component disassembly method when the Horizontal tail is in different positions is studied. When the Horizontal tail is installed on the fuselage, the error is large, and when it is installed on the vertical tail, the error decreases gradually with the increase of height. By using the moment instead of the lift difference method that subtracted from the value of the whole plane configuration, the interference of the Horizontal tail to the wing can be basically eliminated and the interference of the Horizontal tail to the fuselage can be reduced. For the aircraft with T-tail layout, the results obtained by using the component disassembly method combined with the moment inverse calculation are the same as the direct measurement results." @default.
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• W4313444133 date "2023-01-01" @default.
• W4313444133 modified "2023-09-27" @default.
• W4313444133 title "Research on Lift Error of Horizontal Tail Based on Component Disassembly Method" @default.
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• W4313444133 doi "https://doi.org/10.1007/978-981-19-7652-0_41" @default.
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