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A Non-Planar Vortex Lattice Method (VLM) has been combined with a Two-Dimensional Surface Panel Method for computing the aerodynamic characteristics of finite wings in incompressible inviscid flow. This numerical model can be applied to wings with thickness and arbitrary planform, and requires very little computing time when compared to Three-Dimensional Surface Panel Methods currently in use. The formulation of the present method is described in detail, and results from its application to three wing configurations are presented. The results obtained using the present method are compared with results obtained using the VSAERO code and with experimental data. Good correlation is demonstrated in all cases.

Results from a two-dimensional computer model developed at Wichita State University (WSU) for bleed air system analysis are compared with experimental data from icing tunnel tests performed with a wing model equipped with a hot air ice protection system. The computer model combines a commercial Navier-Stokes flow solver with a steady-state thermodynamic analysis model that applies internal flow heat transfer correlations to compute wing leading edge skin temperatures and the location and extent of the runback ice. The icing tunnel data used in the validation of the computer model were obtained at the NASA Icing Research Tunnel using representative in-flight icing conditions and a range of bleed air system mass flows and hot air temperatures. Correlation between experiment and analysis was good for most of the test cases used to assess the performance of the simulation model.