Abstract
Actuator disk models are commonly used for the analysis of rotary wing systems. The blade-element momentum model is probably the most popular one because of its simplicity, efficiency, and good accuracy in many cases. Yet momentum models fail to give satisfactory results in many other cases. The reason is probably the fact that momentum models include a basic assumption that the integral form of the equation of conservation of momentum can be replaced by its differential form. This paper presents a new actuator disk model that does not include the aforementioned assumption. It is assumed that the pressure difference between both sides of each point of the disk is a time average of the pressure difference between both sides of the blade elements that pass through that point. In addition to calculating the axial components of the induced velocity through the disk, the solution procedure also includes calculations of the radial component. The new model includes an iterative solution procedure that converges relatively fast and requires relatively small computing resources and short computing time. The paper describes the new model, presents the solution procedure, and compares the new results with known results from the literature.
Published Version
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