You made a couple mistakes...
1) you are interjecting "slower" into the equation.... That's not part of the equation. In my post I clearly stated "two identical objects in the air except weight". If ALL things are equal except weight the heavier will be more resistant to sudden changes due to inertia.
2) We aren't talking about the aircraft merely being able to fly into the wind but the mass of the aircraft resisting the force of the wind such as in gusts. If the wind (force) were constant we could indeed discount inertia etc but we aren't talking about sustained/constant forward flight.
Usually when this is discussed, it's about smaller, slower drones and larger, heavier drones, rather than drones that are identical except their weight.
Perhaps
@sar104 could comment on the physics involved?
You guys are talking about different things.
First - recall the forces that act on a rotorcraft:
In hover or steady flight, neglecting aerodynamic lift due to the airframe, which is fairly small, the aircraft weight is balanced by the vertical component of motor thrust (labeled "lift" in the diagram above) and the aerodynamic drag is balanced by the horizontal component of the motor thrust ((labeled "thrust" in the diagram above).
In a steady wind field (which is the case that
@Meta4 is referring to) the mass or weight of the aircraft has no effect on its ability to hold position or progress against the wind because no acceleration is involved - it's entirely governed by the maximum airspeed of the aircraft in steady flight.
In an unsteady wind field (
@BigAl07's example) it's potentially much more complicated, since the response depends on the rate of change of the wind speed and direction relative to the rate at which the aircraft can change tilt.
If the aircraft can change tilt fast enough to keep the forces balanced then again - aircraft mass is not a factor and maximum airspeed is all that matters.
Mass comes into play if the changes in wind speed and direction are rapid enough that the thrust vector cannot change fast enough to follow them. In that case the forces on the aircraft will not be in equilibrium and the aircraft will be in unsteady flight. With some simplifying assumptions, the resulting deviation from steady flight becomes a function of rate of change of drag, maximum thrust/mass ratio (maximum available linear acceleration), maximum thrust/moment of inertia ratio (maximum rate of change of attitude) and maximum rate of change of thrust (maximum rate of change of acceleration).