The wall and freestream boundary conditions are trivial   . This is why the model is not sensitive on  outer part of the boundary layer. The behavior of  near the wall is almost linear, thus the solution of equation () does not require thicker mesh than the algebraic model. The model can be used for compressible flows or unstructured grids. Spalart and Allmaras tested the model as well as on boundary layer equations as on RANS. The model was tested and calibrated on RAE 2822 airfoil and in general gives better results than Baldwin-Lomax model.