A fin CFD analysis, not part of the Euler CFD analysis, is automatically performed when the user clicks the

a) Input the first node number that defines the leading edge of the fin-tip chord [c] and then the second node number that defines the trailing edge of the fin-tip chord [d] is automatically displayed in the Fin Mesh Controls region.

b) Input the total number of grid points in the X [axial] and Y [up] directions. Depending on the complexity of the fin shape, the user may need to adjust the total number of grid points in the X and Y directions and the starting node for the fin-tip chord to generate a uniform and solvable fin mesh.

c) Solve the Fin CFD by clicking the SOLVE command button in the Solution Controls region in the Fin CFD Analysis screen.

d) By default AeroCFD computes the flow on the windward side of the fin after clicking the

Background: For subsonic flow this analysis uses thin-airfoil (fin) vortex-sheet theory to determine the pressure distribution (P/Pinf), pressure coefficient distribution (Cp), Mach number distribution (Mn), density distribution (R/Rinf) and temperature distribution (T/Tinf) on the surface of the fin. The Prandtl-Glauert compressibility factor, SQR(1-Minf^2) is used to convert airfoil vortex-theory results to compressible flow results for velocity up to Mach 0.80. For supersonic flow the windward surface distributions are computed using the oblique-shock wave relationships for thin fins. Finally, for supersonic flow the leeward surface distributions are computed using the Prandtl-Meyer expansion wave relationships for thin fins.