airfoil boundary condition
I have written a Fortran program to simulate flow around airfoil:
My problem is: Determination of separation on naca airfoil at low Reynolds numbers (1e3 to 1e5) Flow caracteristics: * Steady, 2D * Incompressible, viscous and Laminar Mathematical model: * Continuity equation * 2 momentum equations Discretization method: * Structured Cgrid generated by "mesh pilot" software * the farfield boundary is 15xcord * transformation of model from physical (x, y) to computational domain (ksi, eta) * Finte volumes discretization * Staggered grid for velocity and pressure * Simpler Algorithm * Second order Upwind scheem for convective terms and central differences for diffusive terms Solution of Algebraic equations: * Sweeping * Thomas Algrithm (TDMA) My program diverges after about 5000 itterations althought i've used low relaxation parameters: relaxation for velocity 4e1 and for pressure 1e1. Is that because i've not well imposed boundary conditions or because of other problems? 
Re: airfoil boundary condition
At those Reynolds numbers, the flow is going to separate very soon after the maximum thickness. The wake flow will be unsteady. I don't have a clue why your solver is diverging  it could be anything from a boundary condition to a coding error to the phase of the moon. But I would definitely consider using an unsteady solver for the problem you are seeking to simulate.

Re: airfoil boundary condition
Discretization method: * Structured Cgrid generated by "mesh pilot" software * the farfield boundary is 15xcord * transformation of model from physical (x, y) to computational domain (ksi, eta) * Finte volumes discretization *
The book by Blazek is an excellent reference about the Finite volume method, thereis no need to transform from physical to computational domains, the finite volume method works directly with the physical domain, I guess you have mixed up different concepts in your code, check the book, it has a CD with fortran code hope that will help 
Re: airfoil boundary condition
I have set the following boundary conditions: on airfoil (low side of comput domain): u=v=0 farfield (upper side of comput domain): u=1, v=0 inflow (left side):du/dksi=dv/dksi=0 outflow (right side): du/dksi=dv/dksi=0 u(ksi, eta) and v(ksi,eta) the compnents of velocity.
Is that the correct way to set boundary conditions? 
Re: airfoil boundary condition
What are you doing with pressure on the boundary?

Re: airfoil boundary condition
I'm using SIMPLER Algorithm which allow to find pressure from velocity

Quote:
hi i am an aerospace engineer....i have to simulate the flow over an airfoil, i have to write a code and i have not enough time to do that... can i borrow your code? i prefer spending my time on a prewritten code and try to modify it for my purpose.. thanks 
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