Not sure of your point there. Strictly an aircraft stalls at an Angle of Attack (AOA) not a 'g' loading. The AoA can be equated to a basic stall speed at 1g which is normally quoted in the manual for straight and level flight (and will depend upon aircraft all up weight).
That basic stall speed increases with the square root of the 'g' not 1.4x1.4Vs.
Therefore, at 2g the aircraft will stall at (squareroot of 2) 1.4142 x basic stall speed.
at 4g the aircraft will stall at (squareroot of 4) 2 x basic stall speed. etc
This equation of IAS and g loading will induce the critcial AoA which will cause the wing to stall. If it could be measured the absolute AoA required to stall the wing is the same whether straight and level or pulling 2g, 3g, 4g etc etc