Parametric study of an aircraft wing hot air anti-/de-icing system using numerical tools

To design efficient anti/-de-icing systems for wing, appropriate conjugate heat transfer (CHT) methodology is helpful. Based on a design of experiment methodology, a parametric study of the heat ratio according to three design variables of the anti-icing system is presented. The anti-icing system geometry consists of a piccolo tube with three rows of round jets inside a swept wing based on NACA23014 airfoil. To model the anti-icing system, a conjugate heat transfer procedure from commercial CFD software is used to solve a cold air external flow, a compressible internal flow and the thermal conduction in the airfoil skin. Based on results available in literature, an appropriate test case for model validation is selected. Then, a description of the RANS equation model applied to a CHT problem and a short description of the finite volume based method are presented. Numerical results are compared against numerical results for a 3D hot air anti-icing. The Box-Behnken design of experiment methodology for three variables will be used to build a second order quadratic model of the heat ratio at the inlet and at the wing leading edge inner wall.