Does anyone have any data or links to technical papers on why the B-36 was built with pusher engines??
I assume that the Convair engineers (and the Northrup engineers working on the B-35) calculated that the drag reduction by not having the propeller airflow over the wing more than made-up for the losses resulting from the propeller having to work in the wake from the wing, but was the difference significant??
I notice that some other 'clean sheet of paper' very long range aircraft (Me 264, and the Nakajima G10N) were conventional tractor designs, so I assume the difference in efficiency between tractor and pusher was pretty close, but that is just a guess.