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At the moment, there is only one stall AOA modelled in the current flight model and it is defined as the alpha where maximum value of Cl is reached in the lift_coef_aoa_table.
However, the stall AOA changes with various variables, notably the Mach number and it could be great to have a table allowing to tune it for different Mach numbers, by scaling it up or down, in the same way the lift coefficient can be tuned via the lift_coef_mach_table.
