Direct numerical simulation with compact high order method (4th order); RE = 1,000,000 and MA = 0.5 is solved over a NACA0012 airfoil with the angle of attack of 10 degree.
MS Thesis is "Transition Prediction Flow with Direct Numerical Simulation over a Flat Plate". In the thesis, 6th order compact scheme with 8th order implicit filtering has been used. In order to reduce memory, 5th order two registered memory Runge-Kutta with 9 steps is used. Parallel programming with MPI has been used to reduce run time.
Two types of waves (two-dimension and three dimension) are added in inflow boundary. In two dimensional added wave the amplitude of disturbances are less than 1% of mean flow; therefore the transition will not start, as shown in the below figure the friction coefficient (Cf) is still laminar.
In addition, for flow over a NACA0012 airfoil, with Re=100,000; Ma=0.2; AOA=4.0. The Vorticity magnitude and the vorticity are shown below.
Also, for flow over a NACA0012 airfoil, with Re=1,000,000; Ma=0.5; AOA=10.0. The Vorticity magnitude and the vorticity are shown below.
Direct numerical Simulation (DNS) of high order (6th order compact) Navier-Stokes was done in my MS thesis, to simulation transition over flatplate.
Non-Reflecting Boundary Conditions (NRBC) have been used. Not only for inflow and outflow, but also in wall boundary condition.
Parallel Programming is one of the necessary conditions for the high performance computing problems. Message Passing Interface (MPI) was used for my MS thesis.
Object Oriented Programming has been used in my program, better structure of program with OOP; better debugging, modification and extension!