Abstract
In order to meet the requirements of the flammable liquid fire prevention regulations under AC25-863, which stipulates that in the event of ignition, the ignition and its harm of leaked flammable liquids should be minimized, this study investigates the impact on the aircraft structure and the suppression process of wing leading edge pool fires of flammable liquid leakage under forced ventilation fire suppression. Geometric modeling of the wing leading edge in the flammable liquid leakage area is performed, and the burning conditions of the flame under different conditions are simulated. The heat release rate per unit area of the pool fire surface is set to 396.67 kW/m, with ventilation speeds ranging from 0 to 3.1 m/s. Through the analysis of simulation charts and data, it is observed that as the forced ventilation rate increases, the pool fire gradually tends towards a trend of suppression
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