Kevin L. Leffel

Numerical Modeling of an Advanced Pneumatic Impulse Ice Protection System for Aircraft

The development of a numerical model of an advanced pneumatic impulse ice protection system for aircraft is described in this paper. A time-dependent, compressible flow model for internal duct flow is used to model the ice protection system, also known as PUP. The model incorporates a high resolution shock capturing method, essentially nonoscillatory (ENO) scheme with subcell resolution (SR) and characteristic direction (CD). The model consists of a constant pressure reservoir, a variable area valve, and a tube section that expands due to the passage of a shockwave. A grid generation scheme is used to account for the size of the system. The model is analyzed for different inlet and exit boundary conditions. Preliminary results are obtained for a range of compressor pressures and the model is shown to give results of practical use. The paper also recommends a suitable operating pressure for the compressor.