Investigation Of Icing Accretion Influences On Aircraft Flight Performance

Icing accretion is very harmful to aircraft flight, and draws much attention to the influence on aircraft flight performance. The condition of icing accretion, the style of icing accretion, the parameters of icing accretion in flight, and the influence of icing accretion on the aerodynamic characteristics of airfoil are discussed firstly in this thesis. The increments of the airfoil aerodynamic coefficients due to the icing accretion are then modeled using an engineering method specially developed in this paper. These increments are transformed and added to the wing and horizontal tail aerodynamic characteristics. Based on this aerodynamic performance of the wing/fuselage/tail configuration, the aircraft flight performance is calculated under ice accretion.Selected test data regarding the aerodynamic forces and moment of airfoils with ice are analyzed and then fitted into polynomials, obtaining nominally universal variations of the lift coefficient, drag coefficient and pitching moment coefficient with angle of attack. In doing so, the aircraft longitudinal aerodynamic characteristics are calculated with three different icing models. The flight performance is investigated of the Fokker 100 which is selected as a calculation example. The influence of the ice models on the flight performance is finally analyzed and discussed.