Numerical Simulation of Eulerian Approach to Heat Transfer Performance of DCCLHPs through Leading-Edge Aircraft for Anti-Icing Applications

Abstract

A numerical model were developed to heat transfer characteristics of a nanofluid on aircraft leading-edge anti-icing applications and predict the optimized flight operating parameters .This simulation presents a Eulerian approaches  to flow the nanofluid with different volume fractions through DCCLHPs  for leading aircraft anti-icing applications. The validation process offered the accuracy of the numerical results when compared with the experimental results.  In Computational Fluid Dynamics (CFD) designed leading-edge structure and boundary meshing leads to diminish the grid sizes and improve the heat transfer performance and develop the wall treatment. The theoretical analysis of calculated surface temperature value is compared with the similar flight data experiments. As a result indicates the surface temperature on leading-edge skins discovered the interactions of hot/cold flow and thermal conductivity of solid to fluid zones. These computational results under the various flight conditions provide valuable suggestions for developing the anti-icing technologies.