Multiblock Navier-Stokes solutions about the F/A-18 wing-LEX-fuselage configuration

The modeled configuration of three-dimensional thin-layer Navier-stokes computations for F/A-18 configuration includes a precise surface representation of the fuselage, leading-edge extension (LEX) and wing, with or without the leading wind deflection. The computational flowfield domain around the subject configuration is decomposed using the multiblock structured grid strategy. The compressible Navier-stokes equations with an upwind-biased, flux difference splitting approach is solved by an algorithm, and the steady state solutions determined.