My Question is this. The F16A models in the US tech tree are equipped with the F100-PW-220 engine. It produces 6490 kgf when spaded. The F-15C is also equipped with the F100-PW-220 engine, but it makes less thrust at 6067 kgf when spaded (both dry). Can anyone explain the 420 kilos of thrust loss?
Even stranger, the F15C engines create 8410 kgf at afterburner (sea level, 0 speed), while the F16A creates 8985. It seems like the F15C is missing a total of 1150 kgf at WEP?
Channel losses are more extreme on the F-15.
Do you think that channel losses account for more than 1000 kilos of thrust lost between both engines at 0 airspeed? and almost 1000 kilos per engine at peak thrust speed?
One jet has a design that moves 2.7 mach of air down to <1 mach.
The other has a design that moves ~2.1 of air down to <1 mach.
The one that has to move faster air down more will have more channel losses.
what was that about the f14, I got halfway through and it disappeared
I need to re-research the statement later and don’t have the time to do it now.
Okay cool. I would have thought that the variable geometry intake of the f15 would have helped with flow at similar speeds as the f16, but I guess not, thanks for helping