The relation between tip vortex strength and induced drag is not a simple one and the suggested advantage is not realised in practice. Meanwhile, a pointed tip has other problems. Some that occur to me:
If the wing has a constant aerofoil profile then a pointed tip will tend to stall first at high angles of attack. This creates turbulence over the ailerons and reduces pilot control at a critical moment. Changing the aerofoil such as twisting downward or "washout" reduces the problem. For example the de Havilland DH.88 Comet racer of 1934 has a fairly pointed wing with no washout - and a notoriously vicious wing-drop in the stall. American replica N88XD has around 2 or 3 degrees (I forget exactly) of washout to try and ease this, with the same being included in the restoration of Comet G-ACSP Black Magic.
But reprofiling the outer section changes the lift distribution to a less efficient one. Widening the tip section can help restore efficiency, as well as further reducing the stall problem.
Structurally, a fine point is both prone to damage and difficult to fit a robust aileron hinge inside. The ailerons have to be moved inboard to a wider part of the wing, which reduces their effectiveness.
The point contributes little lift but significant moment and physical width, so removing it improves aileron and gust responses and eases ground handling, without any significant lift penalty.