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Part 2-3. Aircraft Fuel System Simulation in FloMASTER - Advanced wing tank modeling with venting and inerting


One of the most interesting aspects to the design of an aircraft fuel system, is the complex geometries of the fuel tanks. The fuel tanks are located in the fuselage and wings of the aircraft. The wing tank geometry must fit in the envelope formed by the skin of the wing and the structural struts that support the wings. This paper will look at how FloMASTER’s Advanced Tank components can be utilized to accurately model this complex geometry to get an insight into the venting of these tanks during aircraft maneuvers. Additionally, it will consider the simulation of the fuel tank inerting to prevent in tank fires.

The model that will be discussed is the same as was used in the first two papers of this series.

The first paper, presented the modeling of a typical aerospace fuel system, and introduced the model and performed a few basic but important initial flow studies including: identifying an optimum pipe size for the refueling line, selecting proper flow restrictors to balance flow, and examine transient analysis scenarios to understand the effect of valve closure timing on pressure wave propagation. The second paper took the model a step further and showed how active controls, including a pre-scripted flight profile, could be applied to the model to simulate a complete flight to help achieve the goal of maximum fuel storage in the wing tanks while avoiding complicated piping, or opening the design up to single points of failure such as single isolation valves. If you want more background on this model these papers are available on