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As part of icing certification flight test programs, artificial ice shapes are typically installed onto aircraft fixed leading edges in order to quantify changes to the handling qualities and performance characteristics of the aircraft in icing conditions. Artificial ice shapes allow a test team to evaluate what are generally the worst combinations of flight conditions for different ice protection system configurations. The goal of this paper is to discuss the details behind the design, development, construction, and installation of artificial ice shapes as they pertained to the evaluation of the need for horizontal stabilizer ice protection on the BA609 Tiltrotor with a focus on the extrapolation methods used to design the shapes.

As the technology in rotor deicing matures, more programs are willing to engage in the certification of their helicopters for flight into icing conditions. The S-92A™ helicopter, AW139, V-22, and EC225 aircraft have been certified/qualified recently and are illustrative examples of such engagement. The state-of-the-art configuration definition of rotor ice protection systems that have been introduced into the western rotorcraft manufacturer's production line has been limited to electro-thermal deicing systems. System configurations may use either chordwise or spanwise shedding schemes and could differ in design and operation. Regardless of the selected design configuration, an analysis of the required extent of protection coverage must be performed unless one has access to data offering sufficient similitude in terms of airfoil geometry and flight conditions.