Publication: Experimental study of temperature distribution on bias acoustic liner
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Date
2023-07-13
Authors
Masdiana Najwa binti Masmawi
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Abstract
Aircraft icing can cause serious damage to aircraft, which can lead to crashes. There are number of ways to mitigate aircraft icing, including utilizing electrical thermal deicing to produce heat and melt the ice accumulated on aircraft. Furthermore, to mitigate the engine noise produced by aircraft, a noise abatement tool, Bias Acoustic Liner (BAL) is installed in the nacelle cowl zone, which is the primary source of noise. However, there is limited understanding of how the liner behaves thermally during operational conditions with the ice protection system. Therefore, this research paper aims to conduct an experimental testing and analyze the heat transfer rate of Bias Acoustic Liner (BAL) to facilitate with anti-icing system in aircraft applications. Ten averages of free stream velocities ranging between 0.6 m/s to 2.1 m/s, with ten different heat dissipations ranging from 0.1686 W to 2.6765 W have been examined. Reynolds number recorded in the experiment are ranging from 4800 to 15600. The respective temperature measurements and velocities for this experiment were recorded using thermocouples, data logger and anemometer, where the overall uncertainties for both
systematic error and random error is 5.13 %. Based on the recorded data, it can be observed that the heat transfer coefficient decreases as the heat dissipation is higher. Hence, based on the experiment conducted, it can be indicated that increasing the temperature will lead to a decrease in the heat transfer coefficient. Besides, the heat transfer coefficient and Nusselt number exhibit a proportional relationship with the Reynolds number for all heat dissipation rates. In conclusion, the bias acoustic liner proves to be a highly effective tool for noise reduction and can work efficiently with ice protection system in aircraft.