Figure 14.5. CFD analysis of a 2D aerofoil

14.5 Case Studies

This section includes elementary examples of case studies beginning with 2D cases, as shown in Figure 14.5. The first diagram represents an aerofoil showing the grid layout.

The domain of analysis is large with the anisotropic adaptive grid (Figure 14.5a), which is more dense the closer it is to the LE and trailing edge matching the surface grids and where shocks are present. When the solver has been run, the results can be seen in the postprocessor showing the Mach number isolines (Figure 14.5b). In another run with a different setup, the results are shown in a color spectrum (i.e., the gray-scale version in Figure 14.5c).

The next example is a simple, isolated 3D wing, as shown in Figure 14.6a. Half is shown with a simple grid and the other half is shown in shaded geometry. The drag polar from the CFD analysis is compared with results in Figure 14.6b.

CFD analysis of an isolated fuselage should be easy but internal and external flow through the nacelle (Figure 14.7) can prove to be difficult.

Whereas CFD studies on aerofoils exist, flow-field analysis on nacelles is rare. Chen [17] et al. presented a flow-field analysis over a symmetric isolated nacelle

Figure 14.6. CFD analysis of a wing ([13] – Henley innovations)