10.2 Pressure-Correction Methods for Arbitrary Mach Number
323
Fig. 10.5. Geometry and boundary conditions for the compressible channel flow
Fig. 10.6. Mach number contours in the compressible channel flow (from minimum
Ma = 0.22 at inlet to maximum Ma = 1.46, step 0.02); from Lilek (1995)
Fig. 10.7. Comparison of predicted (Lilek, 1995) and measured (Mason et a]., 1980)
distribution of pressure along
channel wall
The solution method presented in this section tends to converge faster
as the Mach number is increased (except when the CDS contribution is so
large that strong oscillations appear at the shocks; in most applications it
was about go-%%). In Fig. 10.8 the convergence of the method for the solution of laminar incompressible flow a t Re = 100 and for the supersonic
323
Fig. 10.5. Geometry and boundary conditions for the compressible channel flow
Fig. 10.6. Mach number contours in the compressible channel flow (from minimum
Ma = 0.22 at inlet to maximum Ma = 1.46, step 0.02); from Lilek (1995)
Fig. 10.7. Comparison of predicted (Lilek, 1995) and measured (Mason et a]., 1980)
distribution of pressure along
channel wall
The solution method presented in this section tends to converge faster
as the Mach number is increased (except when the CDS contribution is so
large that strong oscillations appear at the shocks; in most applications it
was about go-%%). In Fig. 10.8 the convergence of the method for the solution of laminar incompressible flow a t Re = 100 and for the supersonic