The present work addresses several aspects associated with an efficient use of the high-order Spectral Difference (SD) method for the simulation of compressible flows. Flows of interest are assumed to be adequately modeled by the two-dimensional (2-D) Euler or the 2-D Navier-Stokes equations. Issues associated with the use of an implicit time integration scheme, limiter formulations and curved boundary approaches are discussed. Order of accuracy studies are considered for literature test cases to measure the effective accuracy of the SD method. The results provide data for discussions regarding the coupling of high-order mesh boundaries, implicit time-marching, viscous effects and limiter techniques for the high-order SD method. In particular, the need for the use of high-order meshes at wall boundaries for adequate simulation of flows using high-order SD methods is highlighted and discussed. Furthermore, typical aerospace airfoil flows are also addressed, both with inviscid and viscous formulations, in order to demonstrate the capability implemented.