In the interest of "Keeping it real"
The wing of the P-38 did give it some advatage because of it's high aspect ratio and despite of the engine nacelles placement in the wing. But the question is did it give it better lift than a single engine fighter or a better (lower stall) than a comparable single engine A/C?
P-38L at 15,000lbs from the flight manual stalls clean condition, power off at 94MPH IAS but 109MPH CAS.
That gives it a Clmax of
15,000lbs * 391 / 109MPH^2 * 327sqft
5865000 / 3885087
Clmax= 1.51
Stall speed = 109MPH
So it has a SLIGHTLY higher than average Clmax but a higher than average stall speed as well at a moderate weight.
By comparison
P-51D Clean power off
9,000LBS
Stall speed 101MPH IAS and a CAS Speed of 106mph
9,000 * 391 / 106^2 * 233sqft
3519000 / 2617988
Clmax = 1.34
Low Clmax relative to the P-38. Possibly because of laminar wing?
F4U-1D
11,300LBS
Stall speed IAS 87knots but with a CAS of 85Knots or 98MPH
11,300lbs * 391 / 98^2 * 314
4418300 / 3015656
Clmax = 1.46
That clmax is in line with most WW2 fighters despite the spoiler on the starboard wing.
So despite the variance in Clamx or wing design the fighter with the lowest wingloading still has the lowest stall speed.
How about with full flaps? Does that change anything? Well the equation doesn't work anymore because wing are changes with flaps so I will just list the speeds.
No power
P-38L
15,000LBS
Full flaps Stall
IAS= 69MPH
CAS= +11MPH = 80MPH
P-51D
9,000LBS
Full Flaps Stall
IAS= 94MPH
CAS= +3MPH = 97MPH
F4U-1D
11,300MPH
Full Flaps Stall
IAS = 86MPH
CAS = -2knots = 84MPH
So the P-38 gained all of it advantage through use of it's flaps.
But before anyone draws any conclusions keep in mind that these are the loaded weights of these A/C and I took the weights closest to comparison in the various POH.
P-38L = 17,500lbs -2500lbs to reach 15,000lbs
P-51D = 10,100lbs -1,100lbs to reach 9,000lbs
F4U-1D = 12,175LBS -900lbs to reach 11,300LBS
So draw your conclusions accordingly.