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This paper presents CHT2D, a 2D hot air anti-icing simulation tool developed by the Advanced Aerodynamics group of Bombardier Aerospace. The tool has been developed from two main modules: the ice prediction code CANICE and the Navier-Stokes solver NSU2D, which is used to solve the hot air internal flow. A “weak” coupling beween the two modules based on function calls and information exchange has been priviledged. Three validation test cases are presented: for dry air conditions. Predictions from CHT2D agree quite well with the experiments. Preliminary results are also presented for a test case in icing conditions for different heat loads from the anti-icing system, to study the effect on the accumulated ice.

The Advanced Aerodynamics Department at Bombardier Aerospace is developing a multi-disciplinary methodology for the design of commercial transport wings. The approach taken is to build each component of the methodology in a stepwise fashion from the ground up and integrate the engineering analysis and design tools already in place at Bombardier. Development efforts have been directed to the integration of low and high fidelity computational fluid dynamics codes into the multi-disciplinary environment, the development of conceptual wing structural design codes, wing weight estimation codes, and codes for the prediction of wing static aeroelastic deformation under load. This paper gives an overview of the development and validation of the various components of the methodology and their integration into an engineering approach to multi-disciplinary optimization.

A Transonic Small Disturbance code originally developed at Canadair for the analysis of 3D wing/body/pylon/store configurations (AGARD CP-412-8) has been extended to calculate flows around complete aircraft such as the Challenger Executive Jet. The program uses a modified Transonic Small Disturbance equation discretized in cartesian and cylindrical coordinates and a grid embedding technique to capture flow details around specific components. The equation is solved using a successive line over-relaxation technique applied in two phases. In the first phase, the flow field is relaxed in the overall crude grid and in the winglet cylindrical grid. In the second phase, the crude grid and the various embedded fine grids are relaxed in alternating steps. The interaction between the various grids is through simple linear interpolation.