Well, here is the flight test in July 1944 to evaluate 44-1 at 3000/70"MP.
http://www.wwiiaircraftperformance.org/p-38/p-38-28392.htmlTop Speed = 419mph at 19.8K, at limit speed 26,800 RPM for Turbo. 3000RPM @70" MP.
At critical alttude of 24K top speed was 413mph at 60"MP
The primary advatage was a higher rate of climb with a corresponding trade off of a.) lower speed at escort altitudes, b.) lower ceiling and c.) lower critical altitude.
There NEVER was a 20-25mph increase in top speed for the jump between 130 and 150 octane. Additionally the usual 10-15mph boost of top speeds (17mph in above report) came with a corresponding lower critical altitude. The issue for the P-38 was the turbo limits. Note also that the P-38J-15 for this test was flown in clean (no wing pylons) condition - as most P-38 tests were flown compared to P-51 testing, where most, including the associated 44-1 flight tests were flwn with racks - a 12mph drag penalty but inclusive of all ETO/MTO escort conditions.
Also - the 'potential horsepower available' for each succeeding model was never the issue - it was always the intercooler and turbo issues - not to mention the poor quality 'leaking' ducting design which seems to be mentioned in nearly every P-38 flight test I have seen when 'issues' are discused. Life followed art as that was a constant maintenance write up in ETO