[Nawaf_Ar]

Hello Everyone,
I'm relatively new in CFD so excuse any mistakes, or lack of general knowledge that might appear from this question.

Background:
I'm running a case study on a NACA4412 airfoil (2D with boundaries being 20m from the airfoil in all directions at the least, while the airfoil length is 1m).
The inlet is a velocity inlet of 44m/s to achieve a Reynolds number of 3,000,000.

Purpose:
The purpose of this case study is to check all possible solution methods, and compare their accuracies with published NASA experimental results, compare the convergence time, and deviations. The end result will be a large graph of experimental results of cl vs alpha of all the solution methods for y+1 (from 1 to 5) and see the deviation of each method from the experimental results, including iteration time, and choosing the most optimal. Another case will be the same except this will be for y+ >30 (in my case I'm picking 50-60 as my acceptable range for my mesh). The purpose of this is again to compare the optimal methods, as having a larger y+ would allow me a less refined mesh, and thus much faster computaiton.

Question:
I have gotten convergence from a few solution methods (easiest to converge is SST k-omega). So, will every single solution method converge, and the trick is to manipulate the wall treatments, controls, and methods to reach that? (i.e coupled vs simple, steady vs PTS, first order vs second order, a mix of everything before, hybrid vs standard vs fmg-initialization) etc...
Or will some methods never converge for my case regardless of what variant (standard vs realizable vs rng k-e for example) I choose?

In others words (and I apologize if this has gotten confusing):
Will k-e always converge, and it's just a question of Realizable vs Standard vs RNG?
Will Spalart-Allmaras always converge for this case?
Will k-w always converge and it's just a question of SST vs Standard?

For more clarification, I'm tracking mass flow rate, residuals, cl, cd, cm_c4 for convergence conditions (although cd values aren't focused on as they are 2d). My convergence conditions are residuals no less than x10^-3 with no "jumps", and no significant changes in the aerodynamic coefficients, and a mass flow rate of 0.

Thank you, and apologies for any confusions.