A summary of investigations into predictions of the aerodynamic drag of a modular helicopter fuselage (Eurocopter Dauphin DGV 200) is presented. Drag results are shown for two different configurations, Reynolds numbers up to 6 × 107 (flight conditions), with and without support structure of the wind-tunnel model. Numerical accuracy is investigated for one test case using different computational grids. The results are compared with wind-tunnel measurements and show good agreement with the reference data when the influence of the wind-tunnel strut is taken into account. The computational fluid dynamics model developed consists of a parallel multiblock, multigrid Reynolds-averaged Navier-Stokes code and a three-dimensional hyperbolic grid generator. Block-structured grids are generated from a CAD base. From a numerical point of view, convergence was achieved quickly in all of the cases computed, thus showing efficiency and low CPU cost.