Since the XP-51F carried more fuel in the wing tanks than the P-51B/D, is there a way to figure out what the range on internal fuel would be for those aircraft? I haven't had much luck finding range for the P-51D for example on the wing tanks only. And because the XP-51F (and other lightweight Mustangs such as the P-51H) had more fuel in those wing tanks and even better aero, it should have better range on those tanks.
Also, not directly related to this, the P-82B/XP-82 had a range on internal fuel of 1390 miles. Is that point to point, or radius?
Simple answer for calculated, pre-test, yes. Same engine as the P-51B/C pre March 1944......
What is tricky about this question, specifically, is that THP Available vs THP Required to maintain cruise velocity at a specific altitude requires a.) Thrust HP based on propeller efficiency and RPM for a range of low MP, as well as b.) jet Thrust Hp - are factors influencing specific fuel consumption at different speeds and altitudes.
It is an iteritive, table based set of Integral equation calculations that integrate function of velocity, fuel consumption rate (-->decreasing gross weight) and THPreqd, over Beginning Gross Weight to Final Gross Weight range.
With computers, you are able to vary angle of attack as weight decreases to maintain same V with less drag and less THPreqd as fuel is consumed.
Usually, the factors of warm up at say 1200 rpm, taxi, single ship takeoff at METO MP, climb at Max Continuous HP to cruise altitude, cruise, descend, loiter for 30 minutes - all have defined estimates for the fuel consumption as function of MP/RPM for each stage for P-51B clean.
At a guess, I would offer that the max cruise range point to point for the XP-51F is in range of 1100 mi on usable fuel of about 180gal. at 10,000 feet