The lift force is the weight of the aircraft. The lowest drag point would be where the induced and form drag curves cross each other. The induced drag coefficient (Cdi) is equal to the form drag coefficient (Cd0 in AHT). If you use the coefficients in AHT, solve for CL, you can figure the glide speed and drag force (2 * Cd0) to get an estimate on glide performance.
P-51D (9500 lbs, Aspect ratio = 5.8): CL = 0.57, V = 168 mph, Drag ~ 593 lbs. L/D = 16.0
P-38J/L (17500 lbs, aspect ratio = 8.25): CL = 0.84, V = 158 mph, Drag ~ 1129 lbs, L/D = 15.5
P-47D (14500 lbs, aspect ratio = 5.6): CL = 0.61, V = 176 mph, Drag ~ 1012 lbs, L/D = 14.3
F4u-1 (12000 lbs, aspect ratio = 5.35): CL = 0.67, V = 149 mph, Drag ~ 952 lbs, L/D = 12.6
F6f-3 (12500 lbs, aspect ratio = 5.5): CL = 0.69, V = 146 mph, Drag ~ 990 lbs, L/D = 12.6
Based on those numbers, the P-51 should glide very well. The above figures don't factor in the prop drag.