In this presentation an aerodynamics computational analysis for a partially-dressed, cavity-closed nose landing gear configuration is discussed. The primary objectives of this study are to obtain a full representation of the flow, to compare the computational results against experimental data, to validate the solution and present the capabilities of the software used. For preparing and performing this external aerodynamic analyses, commercial software tools HyperMesh and AcuSolve were utilized, which enable the geometry manipulation, mesh generation and problem solution. AcuSolve is a general purpose CFD solver, applying the Galerking/Least-Square (GLS) finite element methodology to solve the Navier-Stokes equations on an unstructured mesh topology (Hughes et al. 1989, Shakib et al. 1991). In the presented vertical solution, steady state and transient CFD simulations including Spalart-Allmaras and Detached-Eddy Simulation (DES) for turbulence modeling are performed. For this study a 1/4 scale model of a Gulfstream G550 aircraft nose landing gear is investigated, which was already tested in NASA Langley Research Center in Basic Aerodynamic Research Tunnel (BART). All simulations performed yielding very good results, with overall good agreement with the existing experimental data from NASA. In general, key strong characteristics of HyperMesh and AcuSolve, accuracy, efficiency and robustness were presented.