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- W2313221324 abstract "In this paper, the drag prediction method (wake integration method) based on the momentum conservation theorem was applied to the aerodynamic investigations on aircraft model. The wake survey of the model is performed to obtain the basic data to evaluate how applicable the technique is to aerodynamic tests in a relatively small low-speed wind tunnel. In this case, it is important to investigate the effect of the measurement interval by the wake survey. The aircraft model is the same geometry model that was used for the correction wind tunnel test previously. The free-stream velocity is kept to be 30 m/s. The Reynolds number based on the mean aerodynamic chord length is" @default.
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- W2313221324 date "2013-01-05" @default.
- W2313221324 modified "2023-09-24" @default.
- W2313221324 title "A Fundamental Study on Aircraft Model by Wake Measurements in Low-Speed Wind Tunnels" @default.
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- W2313221324 doi "https://doi.org/10.2514/6.2013-1022" @default.
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