Abstract
A method has been developed for calculating the flowfield around complex aircraft configurations using upper-surface blowing (USB). The method is based on a zonal grid generation approach coupled with an Euler flow solver algorithm. In this method the flowfield is divided into a number of non-overlapped regions, each containing a compon- ent of the aircraft such as a wing, a fuselage or a nacelle. H-type grids are generated independe- ntly in each region using a hybrid elliptic/ algebraic grid generation scheme. An explicit finite volume Euler algorithm has been developed that is applicable to the multi-region H-type grids. The present method has been applied to a two-dimensional USB model and a realistic aircraft configuration consisting of a wing/ fuselage with two integrated nacelles. Numerical results indicate that the computational method is effective in predicting the flowfield about USB-type configurations and complex aircraft geometries.
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